Engine Cycle Research Articles

Is the Outflow-Layer Inertial Stability Crucial to the Energy Cycle and Development of Tropical Cyclones?

Abstract This study revisits the issue of why tropical cyclones (TCs) develop more rapidly at lower latitudes, using ensemble axisymmetric numerical simulations and energy diagnostics based on the isentropic analysis, with the focus on the relative importance of the outflow-layer and boundary layer inertial stabilities to TC intensification and energy cycle. Results show that although lowering the outflow-layer Coriolis parameter and thus inertial stability can slightly strengthen the outflow, it does not affect the simulated TC development, whereas lowering the boundary layer Coriolis parameter largely enhances the secondary circulation and TC intensification as in the experiment with a reduced Coriolis parameter throughout the model atmosphere. This suggests that TC outflow is more likely a passive result of the convergent inflow in the boundary layer and convective updraft in the eyewall. The boundary layer inertial stability is found to control the convergent inflow in the boundary layer and depth of convection in the eyewall and thus the temperature of the energy sink in the TC heat engine, which determines the efficiency and overall mechanical output of the heat engine and thus TC intensification. It is also shown that the hypothesized isothermal and adiabatic compression legs at the downstream end of the outflow in the classical Carnot cycle are not supported in the thermodynamic cycle of the simulated TCs, implying that the hypothesized classical TC Carnot cycle is not closed. It is the theoretical maximum work of the heat engine, not the energy expenditure following the outflow downstream, that determines the mechanical work used to intensify a TC.

Simulation based analysis to study the effect of compression ring crown height in ring liner assembly on the performance of four stroke petrol engine

Among different piston rings of an Internal Combustion Engine (IC), the top compression ring-liner assembly shared a momentous amount of the total frictional losses, particularly at the Top Dead Center (TDC) and Bottom Dead Center (BDC) where boundary lubrication subsists. In the present study, the lubrication mechanism in piston ring cylinder liner conjunction for top compression ring using one dimensional Reynolds equation assuming axisymmetric contact was studied. The hydrodynamic and mixed lubrication regimes were taken during the study. Gumbel boundary conditions were used for Reynolds equation solution. For boundary pressure calculation, first, combustion chamber pressure variation was determined, then, interring pressure was calculated assuming orifice volume method by solving mass flow rate through crevice volumes using Runge-Kutta 4th order method. The Reynolds equation was solved using finite difference method. Whole solution process was repeated for different engine speed and crown height of top compression ring to study the effect of them in wear and power loss. First, the solution was found for 3000, 5000 and 7500 RPM keeping constant crown height of 10 µm. Average power loss was found to be increased with the increasing engine speed. There was increased in oil film thickness around mid-stroke with the increased engine speed, but there was no significant change in film thickness with the engine speed at the TDC and BDC positions. Then, the solution was again repeated for different RPM varying the crown height. The compression ring with lower crown height showed the better wear performance by increasing the minimum film thickness in critical zones of engine cycle for all RPM. The crown height of 5,7 and 9 µm gave the minimum power loss (77.89, 163.47 and 297.33 W) for 3000, 5000 and 7500 rpm. Moreover, the power loss in the range of 5-9 µm had no significant differences.

Flow Coefficient and Starting Performance Prediction of Variable Geometry Curved Axisymmetric Inlet

With the development of combined cycle engines, it is urgent to estimate more quickly and accurately the flow capture capacity and starting performance of variable geometry inlets over a wide Mach number range. Based on the flow field and parameter fitting, two prediction methods for the curved axisymmetric inlet with lip translation scheme have been proposed. The method based on the flow field of the reference inlet is more efficient than the parameters-based prediction method, as it can accurately predict the lip translation distance and the corresponding flow coefficient over the entire working range of the inlet without additional numerical calculations. Moreover, the starting Mach number is accurately predicted by the fitting method based on the throat Mach number of the reference inlet, with a relative error of only 0.95% compared to the numerical simulation. The flow coefficient-based method is simple and accurate for predicting lip translation distances with a known starting Mach number, with a relative error of only 1.65% compared to numerical simulations. The prediction approaches can overcome the drawbacks of the standard iterative algorithms and significantly enhance computational accuracy and efficiency.

Aerodynamic performance measurement of a novel variable geometry turbine adjustable guide vane scheme by experimental study

As the key component of new-generation variable cycle engines, the adjustable turbine guide vane's through-flow regulation capability and aerodynamic performance have a significant impact on the performance of the turbine stage and even the core engine. Conventional adjustable guide vanes control the through-flow capability by varying the installation angle and thus inevitably result in a gap clearance, which induces a new source of flow losses. This additional loss can degrade the aerodynamic performance of the variable geometry turbine considerably. Therefore, a novel adjustable guide vane scheme with a rotatable suction surface to regulate the through-flow capability is proposed in this paper and its superiority is verified in a typical small aspect-ratio vane. To this end, a high Mach number annular cascade test rig with high-resolution aerodynamic measurement systems is designed and built to determine the aerodynamic performance of this novel adjustable guide vane as well as a conventional one. The mass flow control capability, the total pressure loss coefficient, the isentropic Mach number at the blade surface, and the static pressure distribution at the endwall are measured for these two schemes, respectively. The flow details and loss mechanisms are also clarified with the aid of CFD. The results show that this novel adjustable guide vane scheme achieves a comparable through-flow control capability with respect to the conventional one, with a total pressure loss reduction of 25%-35% at the measured Mach numbers. The flow details reveal that the novel scheme avoids the large-scale leakage vortex that exists in the conventional scheme and also produces a more uniform exit airflow angle distribution for the downstream rotor.

A novel advanced absorption heat pump (Type III) for cooling and heating using low-grade waste heat

The heat of low-grade can be used to get cooling and heating simultaneously by using the coupling of two absorption heat pumps (conventional/not conventional). This novel advanced absorption heat pump requires three pressure levels to increase and reduce the temperature of useful heat, where desorption/condensation processes are shared at medium pressure, and the two evaporation/absorption processes are developed at low and high pressure respectively. The aim of this proposal is to study this kind of advanced absorption heat pump (Type III) by using the first and second laws of thermodynamics, to determine the energy and exergy coefficient of performances for the whole system by taking into account three scenarios of heat flux rates for both evaporators. The irreversibility and exergy performances for the main components are determined to improve the exergy coefficient of performance. The understanding of reversible Carnot cycles, and the general relationship of energy coefficient of performances at low, medium, and high temperatures for this proposal are analyzed. This advanced absorption heat pump reaches cooling temperatures from 14 to 20 °C and heating temperatures between 80 and 106 °C using water/lithium bromide as a working solution. The energy coefficient of performance of 0.68 is obtained when the higher thermal load of the cooling evaporator than the heating evaporator.

Study on SABRE and rocket-based combined cycle engine

Since the 20th century, countries have been conducting researches on near-spacecraft and have proposed a series of representative space vehicle concepts. This paper reviews the brief history of the development of reusable near-spacecraft and focuses on two combined cycle propulsion modes, SABRE and RBCC, with the goal of improving the performance of future near-spacecraft propulsion systems. An improving idea of combining the RBCC with the SABRE is proposed, and its possibility is discussed by analyzing the specific impulse curve. Two combining configurations of them and design principles are obtained by citing the literature and studying similar configurations. The two designs are also compared and the more optimized one is suggested, so as to offer some inspiration for future studies.

Analysis of variable cycle engines performance in cruising using GasTurb11

Variable cycle engines (VCE) have always been a hot topic in aircraft engine research. Because of its variable thermal cycle characteristics, it has a wide range of optimum operating conditions (altitude, flight Mach number). In this paper, a typical double bypass variable cycle engine is used as the object of study, and the Gasturb11 software is used to simulate the engine in two main modes at different altitudes and Mach numbers, to observe the engine operation performance, as well as the relationship between the range and endurance from the derivation of cruise equation. The results show that VCE has a best thermal cycling pattern for a given altitude and Mach number, and for a range of lift-to-drag ratios, resulting in the longest range or endurance of the aircraft. This paper investigates the relationship between range, endurance and thrust of a variable cycle engine and altitude and Mach number to help make the VCE better suited to the needs of an aircraft with multiple missions, long range and high endurance.

Novel three-dimensional simplified numerical simulation method of a compact precooler for hypersonic precooled air-breathing engine

The revolutionary thermal cycle of precooled air-breathing engines has led to the application of a compact tubular precooler. A novel three-dimensional simplified numerical simulation method for a compact tube precooler is proposed. The unique aspect of this method is the integration of low-dimensional design method of the precooler with three-dimensional simulation technique. The method includes a segmented model to discretize the precooler into sub-precoolers, with corresponding performance calculation programs for circumferential uniform and non-uniform airflows in the circumferential direction. The heat transfer and pressure drop are then simulated using a combination of the distributed heat source method and porous model. The developed method was verified with previous experiments, and showed good agreement. In addition, the flow and heat transfer characteristics of the precooler were investigated under both circumferential uniform and non-uniform inlet conditions. The results show that the radial total temperature distortion intensity at the outlet of the precooler is 0.087 and 0.073 under uniform and non-uniform inlet conditions, respectively. Additionally, the intensity of circumferential total temperature distortion increases from 0.004 under uniform inlet conditions to 0.029 under non-uniform inlet conditions. Overall, this method provides an accurate evaluation of the precooler during the engineering design phase.

Evaluation of the combined driving cycle and its effect on fuel efficiency in a vehicle with an Otto cycle engine

The study proposed to analyze the combined driving cycles and their effect on fuel consumption within the Distrito Metropolitano de Quito. For this, a test protocol was established where the orography of the land, traffic density and road infrastructure of the District were studied. These factors allowed the evaluation of consumption through a global positioning system and a canister in order to systematically travel a set of roads in distance, time, and average speed in a vehicle with an Otto cycle engine. The data was processed through a statistical analysis of minimization of weighted averages. The findings revealed that the combined driving cycle obtained a high reliability (99.7%) in each procedure. The outcome of the study concluded that the combined cycle was differential to that proposed by the manufacturer, since there is a variation of 40% as proposed by the vehicle manufacturer.

Finite-time thermodynamic and economic analysis of Rankine Carnot battery based on life-cycle method

Rankine Carnot battery (R-CB) has a great potential in renewable energy-to-grid integration, and the theoretical thermodynamic performance is inaccurate because of the dynamic heat transfer processes and system performance. In this paper, an R-CB system consisting of a heat pump, a heat engine cycle, and a sensible heat storage tank was established. The finite-time thermodynamic model considering the irreversible loss of energy transfer and conversion processes was proposed. Based on the combination of finite-time thermodynamic model and life-cycle method, the levelized cost of energy storage model was established for the combination of economic and energy performance. Furthermore, evaporation temperature, heat storage temperature, temperature difference of shared heat exchanger, and shared heat transfer area were adopted as main variables to conduct the global optimization and parametric analysis of the system. The simulation is based on an R-CB system with a storage capacity of 10 MW/6h, and the results showed the optimized system roundtrip efficiency was 78.1%, and the levelized cost of storage (LCOS) was 0.329 $/kWh with an evaporation temperature of 100 ℃. The roundtrip efficiency increased from 25.6% to 78.1% with the evaporation temperature rising from 60 to 100 ℃, while LCOS decreased by 45.8 %. Reducing the highest heat storage temperature effectively increased the roundtrip efficiency and reduced the heat storage cost, while decreasing the LCOS. The increase in roundtrip efficiency, which was obtained by reducing the shared heat exchange temperature difference and increasing the shared heat transfer area, was the primary factor in reducing the LCOS. The combination of finite-time thermodynamics and the life-cycle method in this paper may provide a more realistic evaluation approach for measuring the technical and economic potential of R-CB systems.

Technical and economic efficiency of the unconventional propulsion units use for civilian aircraft of various purposes

In order to develop a methodological apparatus for assessing various stages of the life cycle of hybrid/electric propulsion units, the existing approaches to estimating the costs of developing, manufacturing and operating aircraft engines of the traditional propulsion units scheme for determining the cost framework and their further harmonization with the technical and economic boundary conditions of new elements in the hybrid/electric SU scheme are considered. The relevance of solving the problems of assessing the technical and economic efficiency and forecasting the cost of hybrid propulsion units is determined. To solve the tasks, a methodological approach to determining boundary conditions and criteria is proposed. Within the framework of this methodological approach, a preliminary assessment of the cost of the main stages of the life cycle of aircraft engines for various variants of traditional propulsion units was made. Based on the estimates obtained, criteria for the economic efficiency of using a hybrid propulsion unit of various capacities for civil aircraft were formed. A computational and parametric analysis of the cost estimation of variants of aircraft engines included in the propulsion unit of the traditional scheme is presented. The role of accounting and management accounting data in economic and mathematical models is determined, which makes it possible to qualitatively reflect the economic efficiency of the life cycle of aviation products.

Experimental investigation of gamma Stirling refrigerator to convert thermal to cooling energy utilizing different gases

In recent years, combined cooling, heat, and power (CCHP) systems have attracted increasing attention worldwide. Owing to their advantages of high overall thermal efficiency, fuel flexibility, low noise and vibration, and low emissions, Stirling engines are promising candidates for micro-CCHP systems. The Stirling Cycle is one of the thermodynamic cycles that is close to the Carnot cycle in terms of theory, and these advantages cause to use of Stirling engines in wide industries. The main objective of this research is an experimental investigation of the Stirling Gamma engine for refrigeration. In this investigation, the effect of working fluid air and Helium, the operating pressure of the working fluid, and dynamo power on refrigeration generation have been investigated. Results show that using air fluid with a power of 520.8 Watts and operating pressure of 3 bar in 10 minutes could reach to the temperature of -23° Celsius and using Helium fluid with a power of 420 Watts and operating pressure of 6 bar and in 10 minutes could reach to temperature -21° Celsius. In the experimental implementation, it has been tried to reach lower than 10 % error results in various parts of the engine like insulation, leaking, belt lash, and measurement devices. Results show that increasing power supply, mean gas pressure, power supply turning on duration, and using fluids such as air and helium are effective in refrigeration. Also, by using helium instead of air, the amount of cooling output and engine output power decreases while engine efficiency increases.

Development and demonstration of strategies for GHG and methane slip reduction from dual-fuel natural gas coastal vessels

Low Pressure Dual Fuel (LPDF) marine engines fueled with natural gas (NG) provide a cost-effective means for minimizing fuel sulfur content, and NOx and PM emissions for marine vessels. In addition, the use of NG can provide significant GHG reductions, if CH4 slip is mitigated. Alternative fueling strategies such as LPDF, are commonly assessed by life-cycle analyses using exhaust emission rates from generalized engine test cycles (e.g. IMO E2). As CH4 slip from LPDF NG engines is particularly sensitive to engine load, a greenhouse gas emission inventory based on generalized engine cycles may not accurately represent real-world vessel operation and emissions. The objectives of this work are to: (i) quantify the GHG emissions reductions possible using the current best available LPDF technology and, (ii) evaluate the attained real-world emissions reduction as a result of improved vessel operating strategies and state of the art engine technology for coastal LPDF vessels.Steady-state emission factors (g/kW-h) and emission rates (g/h) of CH4, CO, CO2, and NOx were measured during steady-state and dynamic operation for two roll-on-roll-off ferries with LPDF engines from two different manufacturers. During commercial operation, the combination of a revised LPDF engine calibration and best vessel operating strategy reduced GHG emissions by 57% and 24%, relative to stock LPDF and diesel operation on vessel #1, respectively. Compared to diesel operation, the annual GHG savings on vessel #1 as a result of this program equate to approximately 2.4 kT CO2e. The tank-to-wake CH4 emissions measured in the current and previous works were found to have poor agreement with the those based on the corresponding test cycle (E2). The E2 cycle overestimated the current CH4 emissions by 8–30% depending on the implemented operating strategy. Prior to implementation of these strategies, the E2 cycle underestimated the CH4 emissions by 74% (Peng et al., 2020). This underscores the value of in-use emission measurements for accurate evaluation of alternative fueling strategies, as well as the utility of emission-informed vessel operation strategies.

The p38/MK2 Pathway Functions as Chk1-Backup Downstream of ATM/ATR in G2-Checkpoint Activation in Cells Exposed to Ionizing Radiation

We have recently reported that in G2-phase cells (but not S-phase cells) sustaining low loads of DNA double-strand break (DSBs), ATM and ATR regulate the G2-checkpoint epistatically, with ATR at the output-node, interfacing with the cell cycle through Chk1. However, although inhibition of ATR nearly completely abrogated the checkpoint, inhibition of Chk1 using UCN-01 generated only partial responses. This suggested that additional kinases downstream of ATR were involved in the transmission of the signal to the cell cycle engine. Additionally, the broad spectrum of kinases inhibited by UCN-01 pointed to uncertainties in the interpretation that warranted further investigations. Here, we show that more specific Chk1 inhibitors exert an even weaker effect on G2-checkpoint, as compared to ATR inhibitors and UCN-01, and identify the MAPK p38α and its downstream target MK2 as checkpoint effectors operating as backup to Chk1. These observations further expand the spectrum of p38/MK2 signaling to G2-checkpoint activation, extend similar studies in cells exposed to other DNA damaging agents and consolidate a role of p38/MK2 as a backup kinase module, adding to similar backup functions exerted in p53 deficient cells. The results extend the spectrum of actionable strategies and targets in current efforts to enhance the radiosensitivity in tumor cells.

Lubrication failure analysis of camshaft bearings in V6 diesel engine

This contribution investigates the lubrication characteristics and failure causes of camshaft bearings belong to a V6 diesel engine. Numerical simulation based on the theory of elastohydrodynamic lubrication and flexible multibody dynamics is performed to analyse the lubrication characteristics of camshaft bearings. The results reveal that lubrication performance of different bearings of camshaft shows great differences. For a certain bearing, the mixed lubrication state and elastohydrodynamic lubrication state alternately occur in one engine cycle. The duration of mixed lubrication varies greatly in different bearings. For the bearing closest to the timing drive gear, the total pressure is dominated by the asperity contact pressure, and the predicted safety factors of the asperity contact pressure, hydrodynamic pressure and oil film thickness are less than 1, which means that this bearing will have lubrication failure.

A comprehensive study for the identification of the requirements for an optimal H2 combustion engine

As part of the fight against global warming and to achieve greenhouse gas emission targets, it is crucial to reduce the carbon footprint of ground transportation. Mobility needs are continuously growing with increase in population. All these factors will lead to an upsurge in the energy demand for the mobility in the very next future. Consequently, the diversification of low carbon energy sources is urgently required. Hydrogen can be used for mobility solution in its two energy conversion mechanisms: The Fuel Cell technology or the Internal Combustion Engine (ICE). The latter option, studied in the present work, offers the advantages of current fossil fuel engines – existing and proven technology, lifetime, controlled cost – with a very low carbon footprint. The overall objective of the study is to define the specifications of a dedicated Hydrogen direct injection combustion system for ground transportation application with the best fuel efficiency and lower raw emissions, to minimize the aftertreatment needs. A complete experimental and numerical study was carried out to get valuable information on various phenomena occurring throughout the engine cycle. The very first step of the study consisted in performing experimental investigations. For this purpose, an all metal single cylinder engine originally designed for gasoline spark ignited combustion (tumble air motion, gasoline direct injection) was modified for hydrogen direct injection combustion. The gas-gas injection was experimentally studied in the High Pressure/High Temperature vessel available at IFPEN. Those experiments were used to calibrate the 3D CFD numerical approach. Based on a 0D pre-study (boundary conditions) and using the injection modeling calibration introduced before, 3D CFD simulations have been then carried out with specific hydrogen kinetics properties. Finally, this comprehensive study highlights the specificities of ICE running with hydrogen. It provides indications and guidelines for further developments and optimization of hydrogen combustion engines.

Measurement-based quantum Otto engine with a two-spin system coupled by anisotropic interaction: Enhanced efficiency at finite times.

We have studied the performance of a measurement-based quantum Otto engine (QOE) in a working system of two spins coupled by Heisenberg anisotropic interaction. A nonselective quantum measurement fuels the engine. We have calculated thermodynamic quantities of the cycle in terms of the transition probabilities between the instantaneous energy eigenstates, and also between the instantaneous energy eigenstates and the basis states of the measurement, when the unitary stages of the cycle operate for a finite time τ. The efficiency attains a large value in the limit of τ→0 and then gradually reaches the adiabatic value in a long-time limit τ→∞. For finite values of τ and for anisotropic interaction, an oscillatory behavior of the efficiency of the engine is observed. This oscillation can be interpreted in terms of interference between the relevant transition amplitudes in the unitary stages of the engine cycle. Therefore, for a suitable choice of timing of the unitary processes in the short time regime, the engine can have a higher work output and less heat absorption, such that it works more efficiently than a quasistatic engine. In the case of an always-on heat bath, in a very short time, the bath has a negligible effect on its performance.

Investigation on geometric throat matching characteristics of variable geometry rocket-based combined cycle combustor

One of the most effective ways to realize multi-mode and high-performance matching operation of rocket-based combined cycle (RBCC) engine is to adopt a variable geometry combustor. In this study, direct-connect experiments and three-dimensional numerical simulations were used to investigate the matching characteristics between the isolator and the geometric throat of the variable geometry rocket-based combined cycle combustor under Ma 6 condition. The influences of equivalence ratio and geometric throat height variations on the combustor matching characteristics were obtained. The study results show that: (1) The pressure in the combustor and the outlet pressure of the isolator increase gradually with the increase of equivalence ratio, which causes the pre-combustion shock train position in the isolator to move forward gradually. Meanwhile, the combined injection of secondary fuel with the isolator and the pylon is beneficial to the improvement of combustor pressure, thus further improving the engine performance. (2) Different geometric throat heights have a substantial impact on the isolator and combustor matching when the equivalent ratio of the combustor is fixed. Under the conditions of Ma 6 operating at an altitude of 24 km inflow, the starting position of the pre-combustion shock train in the isolator is precisely at the isolator entrance, and the corresponding geometric throat height is 2.10H. The isolator and the combustor can complete matching operation at this point which the geometric throat height is the minimal throat height for Equivalent ratio = 1.0. (3) The reduction in geometric throat height can result in an increase in combustor pressure but a loss in combustor heat release and combustion efficiency of fuel combustion, which are reduced by 21.1% and 7.2% respectively. (4) The heat release and combustion efficiency in the combustor will decrease with a decrease in equivalent ratio at the minimal throat height condition where the isolator and the combustor can complete matching operation. This happens when the equivalent ratio and the geometric throat height change synergistically.

Exploration of acceptable operating range for a compression system in a double bypass engine

The variable cycle engine is distinguished by its highly adjustable compression system, whose aerodynamic characteristic is extremely complex. To explore the regulation range of a double bypass engine compression system, a multi-dimensional analysis method is developed, through which the coupling mechanism between the compressor component and the bypass is examined. The operation zones of the compressor components and the bypass system are proposed, and the operation range of the compression system is obtained by calculating the overlapping part of the operation zones. The results show that in the double bypass mode, there exists a minimum mode selector valve area and a minimum core driven fan stage stall margin that ensures a feasible bypass flow, the two parameters correspond to each other. Under the given fan and core driven fan stage conditions, the maximum value of the inner bypass ratio is restricted by the upper limit of the forward variable area bypass injector and the maximum Mach number in the total bypass, while the minimum value of the inner bypass ratio depends on the lower limit of the forward variable area bypass injector geometry and the system recirculation margin. The single bypass mode is a unique condition of the double bypass mode, as the operation zone of the compressor component degenerates from a two-dimensional surface to a straight line. There are multiple bypass states available in the single bypass mode, while the regulation range of the bypass ratio is jointly restricted by the operation range of the high pressure compressor and the aerodynamic boundary of the forward variable area bypass injector.

The history of flight safety: methodology, experience, prospects

The formulation of the flight safety history problem is stated. The article shows that it is problematic to scientifically substantiate, systematize, analyze and generalize the theoretical and empirical flight safety material accumulated in various fields. From a historical perspective, the necessity for a socio-humanitarian assessment of the transformation processes of scientific and applied experience in the field of flight safety is substantiated. New multidisciplinary line of research, making use of a specific scientific apparatus and methodological tools, i.e., the history of flight safety, the subject basis of which covers social activities throughout the life cycle of all aerospace engineering (artificial flying objects in the Earth's atmosphere and space, aircraft, crews, passengers, other aerospace system specialists), including aeronautics, aviation, cosmonautics over a span of the entire history of mankind, is proposed. A brief overview of publications on the issue of flight safety is offered. The experience of flight safety history research is analyzed. The periodization of flight safety history in the XX–XXI centuries, giving prominence to three stages: 1. Generating ideas, technologies, flight safety systems (10–40s of the XX century). 2. Establishing the national and international systems to ensure flight safety, scientific research, personnel education and training in the field of flight safety (50–80s of the XX century). 3. Developing new ideas, technologies, projects, flight safety management systems, active ensuring of flight safety, etc. (since the 90s of the XX century), is proposed. The foundations of the conceptual model of the flight safety history are presented, the methodology, experience and prospects of research are considered. It is recommended to organize systematic studies of the flight safety history, covering the aspects of the world and domestic science, education and practice; to create a unified information system on the history of flight safety based on new information technologies, the ultimate aim of which can be a virtual worldwide museum of flight safety; to initiate a pilot project of the National Flight Safety Museum of Russia and to start its development in the year of the 100th anniversary of our civil aviation; in the future, to develop a new academic discipline "History of Flight Safety" for training aerospace industry specialists and researchers.