CN116307402A - Comprehensive energy system evaluation method based on flight/transmission cooperative control strategy - Google Patents
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Abstract
A comprehensive energy system evaluation method based on a flight/transmission cooperative control strategy relates to an advanced aviation power comprehensive energy system. The comprehensive energy system with the multi-source energy extraction mode is taken as a research object, and the performance evaluation of the comprehensive energy system is realized through the comprehensive evaluation of the flight/emission level of a typical TBCC engine. The method comprises the following steps: 1) Parameter initialization: 2) Establishing an aircraft dynamics model; 3) Establishing a combined engine model; 4) Establishing a comprehensive energy system model; 5) And solving the optimal track. And (3) quantitatively analyzing the performance influence of different energy extraction modes on the combined power to realize comprehensive evaluation of a comprehensive energy system with a multi-source energy extraction mode. The method combines the flight/emission coordination control of the optimal track and the minimum fuel consumption under a certain energy requirement, uses the influence of the comprehensive energy system on the performance of the combined power device as an evaluation index to establish an evaluation method, and provides a reference value for a future comprehensive energy management system design method.
Description
Technical Field
The invention relates to an advanced aviation power comprehensive energy system, in particular to a comprehensive energy system evaluation method based on a flight/transmission cooperative control strategy.
Background
The development of aerohypersonic aircrafts and combined power technology enables wide-speed-range flying and long-endurance flying to be possible, and therefore the extraction, utilization and management of airborne energy in the long-time flying process become particularly important. Due to factors such as the specificity of the working environment, quality penalty and the like, hypersonic aircrafts are difficult to carry enough power supply equipment to meet the power requirements of all airborne equipment. Therefore, how to reasonably realize the self-sufficiency of electric energy under the limited condition is a great difficulty in energy management of the air suction hypersonic aircraft.
In view of the energy extraction problem, the method has important significance for the aircrafts carrying out long-endurance and wide-speed-range flight tasks, developed countries such as the United states and Russia sequentially put forward concepts related to the comprehensive management of the energy of the aircrafts, and meanwhile, technological researches related to an airborne energy system are paid attention to, and certain achievements are achieved. The relatively mature energy extraction schemes that are common today are mainly the following: firstly, extracting shaft work through a turbine of an engine; secondly, extracting the total enthalpy of air intake/oil gas of the engine by using a turbine; thirdly, based on the thermoelectric conversion device, the aerodynamic heat recovery and utilization are carried out on the wall surface of the engine and the like; fourth, fuel oil cooling
Turbine power generation based on fuel pyrolysis gas (Li, qin Jiang, gan Jianzhou, etc. air breathing hypersonic aircraft energy management and utilization state of the art overview [ J]Flying missile 2021 (7): 12-17).
The conversion efficiency and the applicable working speed range of different energy extraction schemes are different, so that the combined power applied to the wide-speed range flight needs to establish a comprehensive energy system, and the energy requirements of the aircraft in different speed ranges are met in a multi-source energy extraction mode. However, the energy extraction modes can all affect the performances of the combined power device such as fuel consumption, turbine power compressor stability margin, punching power air intake stability margin, combustion stability and the like, and the degree of influence on the combined power is different from the influence mechanism. Therefore, under a certain energy requirement, in order to help the combined power device to realize a lower fuel consumption rate, a suitable evaluation method is found, and it is necessary to quantitatively analyze the performance influence of the integrated energy system on the combined power device.
Disclosure of Invention
The invention aims at providing a comprehensive energy system evaluation method based on a flight/hair cooperative control strategy aiming at an advanced aviation power comprehensive energy system. The comprehensive energy system with the multi-source energy extraction mode is taken as a research object, and the performance evaluation of the comprehensive energy system is realized through the comprehensive evaluation of the flight/emission level of a typical TBCC engine.
The invention comprises the following steps:
1) Parameter initialization: setting target required power and initial conditions (flying height, mach and the like), dividing the flying stage into segmentation points (Ma 2 and Ma 5) by combining the characteristics of the combined engine, setting constraint conditions and control quantity, and giving a reasonable initial parameter range.
2) Establishing an aircraft dynamics model: considering the track characteristic influence of a vertical plane climbing section, regarding the aircraft as a particle model moving on a vertical plane, simplifying a six-degree-of-freedom model of the aircraft according to requirements, and establishing a state differential equation of each state parameter;
3) Establishing a combined engine model: under a certain flight working condition (Mach number Ma/height H), a dynamic model of a typical TBCC engine is established, and finally, the attack angle change rate and a TBCC throttle lever are used as control quantities to be combined with an aircraft dynamic model;
4) Building a comprehensive energy system model: three energy extraction modes are established for the flight speed domains of Ma 0-7 so as to be applicable to different working speed domains; the power generation mode of extracting shaft work by a high-pressure shaft of a turbine engine is adopted in the stages Ma 0-2 (including Ma=2); stages Ma 2-5 (containing ma=5) drive an air turbine to generate electricity by leading air out from the outlet section of the air inlet channel; in the stage Ma 5-7, air is led out from the section of the outlet of the air inlet channel and then combusted by the power generation combustion chamber, and then the turbine is driven to generate power;
5) Solving an optimal track: solving an optimal flight path of the aircraft based on a Gaussian pseudo-spectrum method, setting the flight altitude, the speed, the climbing angle, the aircraft quality and the attack angle as state parameters by combining the model, setting the attack angle change rate and a TBCC throttle lever as control amounts, expressing the optimization problem of the climbing path as corresponding cost functions and parameter limits, and taking the minimum fuel consumption as a performance index; and outputting an influence rule of the call of the comprehensive energy system based on the optimal track on the overall performance of the combined power according to the optimal result, and finishing the evaluation of the comprehensive energy system based on the flight/emission cooperative control strategy.
In step 3), the specific steps of establishing the combined engine model may be:
(1) Establishing a combined engine air inlet channel model:
selecting an axisymmetric air inlet, and calculating performance parameters such as a total pressure recovery coefficient, a flow capture coefficient, a resistance coefficient and the like of the model according to given inlet conditions and air inlet design parameters to obtain outlet parameters of the air inlet;
(2) Establishing a turbine engine working model:
calculating the air flow parameters of each section of the engine and the performance parameters such as unit thrust, fuel consumption rate, specific impulse and the like of the engine through working process parameters, and calculating the thrust of the turbine engine by combining the captured air flow;
(3) Establishing a working model of the ramjet engine:
the thrust and specific impulse of the engine are calculated through the thrust and specific impulse characteristics of the unit flow, only the Mach number effect is considered, the height and the throttling characteristics are not considered, and the unit flow thrust and the specific impulse can be obtained through modeling according to a known change rule.
In step 4), the integrated energy system model is built as follows:
(1) Turbine shaft work extraction model: and a certain required power is extracted from a high-pressure shaft of the turbine engine, and the motor is driven to generate electricity through a transmission device.
(2) Air turbine power generation model: on the basis of total temperature, total pressure and flow of incoming flow at the outlet of the air inlet channel, a turbine working model is introduced to reversely solve the required target power to obtain the flow of air to be led, and the influence of the air-led on the overall performance of the current combined ramjet engine is calculated in an iterative mode.
(3) Gas turbine power generation model: and (3) leading out gas at the outlet of the air inlet channel, burning the gas through a combustion chamber, introducing a turbine working model to reversely solve the required target power on the basis of the total temperature, the total pressure and the flow of the gas to obtain the flow of the gas to be led, limiting the total temperature of the outlet by 2200K, and then iteratively calculating the influence of the gas to the overall performance of the current ramjet engine.
The invention has the following outstanding technical effects:
compared with the existing evaluation method, the method is applied to the TBCC engine, and the performance influence of different energy extraction modes on the combined power is quantitatively analyzed, so that the comprehensive evaluation of the comprehensive energy system with the multi-source energy extraction modes is realized. The invention combines the flight/emission coordination control of optimal track and minimum fuel consumption under a certain energy requirement, and provides a certain reference value for a future design method of the comprehensive energy management system by using the comprehensive energy system to influence the performance of the combined power device as an evaluation index.
Drawings
FIG. 1 is a schematic diagram of an integrated energy system architecture based on a parallel TBCC engine.
Detailed Description
The invention will be further illustrated by the following examples in conjunction with the accompanying drawings.
It should be noted that certain terms are used throughout the description and claims to refer to particular components. Those of skill in the art will understand that a person may refer to the same component by different names.
The embodiment of the invention provides a comprehensive energy system architecture (shown in figure 1) with a multi-source energy extraction mode based on a parallel TBCC engine. Specifically, the comprehensive energy system combines the power characteristics of a parallel TBCC engine, and matches corresponding energy systems for different sub-components: the method comprises the steps of extracting high-pressure shaft work of a turbine engine for power generation, carrying out air turbine power generation by bleed air of a ramjet isolation section, and driving the turbine to generate power by combustion of the bleed air of the ramjet isolation section through a power generation combustion chamber.
The embodiment of the invention establishes a comprehensive energy system evaluation method based on a flight/transmission cooperative control strategy according to the architecture shown in fig. 1, and a specific embodiment is given below, which specifically comprises the following steps:
1. parameter initialization
Setting target required power and initial conditions (flying height, mach and the like) of the comprehensive energy system, dividing the flying stage into segmentation points (Ma 2 and Ma 5) by combining the characteristics of the propulsion system, setting constraint conditions and control quantity, and providing a reasonable initial parameter range.
2. Aircraft modeling
The method is characterized by comprising the steps of establishing an aircraft dynamics model, mainly considering the track characteristic influence of vertical plane acceleration climbing and cruising, so that the aircraft can be regarded as a point quality model of motion on a vertical plane, simplifying the model according to requirements based on a six-degree-of-freedom dynamics model of the aircraft, and establishing a state differential equation of each state parameter as follows:
wherein h represents the altitude, V represents the speed, gamma represents the angle of ascent, alpha represents the angle of attack, T represents the thrust, D represents the drag, L represents the lift, I sp The specific impulse is denoted, m denotes the mass of the aircraft, r denotes the distance of the aircraft from the centre of the earth, g denotes the gravitational acceleration, and the superscript represents the differential of this parameter.
The lift L is defined as:
L＝qSC L (α,Ma)
resistance D is defined as:
D＝qSC D (α,Ma)
wherein q is the dynamic pressure of the flight, S is the reference wing area of the aircraft, and the lift coefficient C L And coefficient of resistance C D Both as a function of angle of attack α and mach number Ma.
3. Engine modeling
Namely, a combined engine model is established, and the following simplified description is made in the calculation process of the model: since the combined engine works in the stratosphere and the atmospheric temperature is relatively constant, the thrust per unit flow and the specific impulse characteristics only consider the Mach number influence, and the height and the throttling characteristics are not considered.
1. Axisymmetric air inlet channel model
Obtaining the total inlet air temperature T of the incoming flow according to given incoming flow conditions and inlet channel design parameters t0 With the total pressure P of the inlet air t0 And an inlet air flow function q (lambda). Because the energy extraction mode of the invention relates to incoming gas extraction, the actual capture flow q of the air inlet channel is calculated according to the requirements of the design points of the engine:
wherein the air flow metering constant K a = 0.04042, flow capture coefficient
Only the mach number effect is considered.
2. Turbine engine working model
The turbine engine model consists of an axisymmetric central cone air inlet channel, a turbine gas generator and a tail nozzle. Because the working speed domain Ma 0-2.5 of the turbine engine has transonic domain flight from subsonic to transonic, the condition modeling is carried out for different flight states (subsonic, transonic and supersonic):
in the sub-and trans-sonic speed (Ma<1.1 The engine flow is determined by the demand of the gasifier, and the flow exceeding the demand is regarded as overflow. In a given inlet ductRelative length L of heart cone in, And total pressure loss coefficient of the air inlet channel, and adjusting the oil-gas ratio f of the combustion chamber to enable the outlet temperature of the main combustion chamber to reach the highest value
And then limiting the relative conversion rotation speed n cor,r Relative physical rotational speed n r Determining the high-pressure shaft rotation speed n by combining the throat area critical of the spray pipe TH 。
When supersonic speed (Ma is more than or equal to 1.1), the flow of the engine is mainly determined by a supersonic speed air inlet, the inlet air flow of the gas generator mainly depends on the working state and the flight working condition of the air inlet, and the outlet temperature of the main combustion chamber reaches the highest value through the oil-gas ratio f of the main combustion chamber
In combination with the determined high-pressure shaft rotational speed n H Calculating the final thrust T tur Specific impulse I sp, High pressure shaft work P C 。
3. Working model of ramjet engine
The ramjet engine comprises two working modes of a scramjet engine and a scramjet engine, and the structure of the scramjet engine can be divided into relatively independent parts according to a pneumatic thermodynamic process: axisymmetric central cone air inlet channel, sub-combustion/super-combustion chamber and tail nozzle.
The thrust and specific impulse characteristics of the ramjet can be obtained by calculating the thrust and specific impulse characteristics of a unit flow, wherein the combined ramjet in a wide speed range works in a stratosphere, and the atmospheric temperature is relatively constant, so that the thrust and specific impulse characteristics of the unit flow only consider the Mach number influence, and the height and the throttling characteristics are not considered.
By ramjet thrust F s Specific impulse I sp With Mach number M 0 The change rule of (2) obtains a fitting relation, and when the actual capture flow q of the air inlet channel is combined, the thrust and specific impulse of a single ramjet engine are as follows:
T total ＝q·F s
I sp,al ＝q·I sp
4. modeling of energy systems
Namely, a comprehensive energy system model is built, and the following models are correspondingly built by combining the characteristics of different sub-components in an engine model:
1. turbine shaft work extraction model (Ma 0-2, ma=2)
When the turbine engine works, certain power is extracted from the high-pressure shaft of the engine, and the main generator is driven by the transmission device to generate power, so that the power is supplied to electric equipment on an aircraft.
P＝P H,ext ·η
Wherein eta is the loss coefficient of the mechanical transmission device and the generator. The power balance equation in the turbine engine model becomes
2. Air turbine power generation model (Ma 2-5, ma=5)
The air turbine power generation model carries out internal air entraining from the outlet of the air inlet channel of the sub-combustion/super-combustion ramjet engine, pushes the turbine to expand and do work, carries out energy conversion through the generator, and finally is discharged into the atmosphere.
The bleed air flow required by the turbine to do work can be quantitatively analyzed by the following formula:
wherein T is t For total temperature of inlet air of turbine, C p Constant pressure specific heat, W, of turbine inlet air T,cor Power, η required for turbine shaft T Is turbine efficiency,
(π T For turbine pressure ratio, K g =1.33 is the gas specific heat ratio), the present invention considers that the above turbine characteristic parameters only vary with the mach number Ma in order to simplify the turbine model.
The turbine work is mainly used for running of a power generation system and loss of a transmission device, so that the following equation exists according to power balance:
P E ＝q 2 W T,cor η m
wherein P is E The power is required for power generation; q is the airflow flow; w (W) T,cor Output power for the turbine; η (eta) m Is the power generation loss coefficient.
3. Gas turbine power generation model (Ma 5-7)
The gas turbine power generation model is different from an air turbine in that the bleed air flow firstly enters a combustion chamber to be mixed with fuel oil for combustion, and then the gas is utilized to do work on the expansion of the turbine. Therefore, in the power balance stage of the turbine expansion work model, the influence of fuel oil mixed in a combustion chamber needs to be further considered, and the turbine output power is calculated as follows:
P E ＝(1+f)q 2 W t η m
wherein f is the oil-gas ratio.
5. Solving the optimal track
By adopting the Gaussian pseudo-spectrum track optimization method, the fuel consumption or voyage of the aircraft can be analyzed based on the optimal track, so that the comprehensive evaluation of the combined dynamic performance is realized.
Based on the aircraft/propulsion system model, the state parameters are: fly height h, speed V, climb angle γ, aircraft mass m, and angle of attack α; the control variables are: rate of change of angle of attack
Throttle lever, etc. Wherein the rate of change of angle of attack->
As the control amount, the purpose is to ensure smooth flight. The state parameters among the endpoints of each flight stage (Ma 0-2, ma 2-5 and Ma 5-7) should meet the requirement of |x i -x i-1 And the I is less than or equal to epsilon so as to ensure that the parameter continuity of each stage is satisfied.
Based on the aircraft control equations, the optimization problem of the climb trajectory can be expressed as a corresponding cost function and parameter limit. The performance index of the invention is that the fuel consumption of the whole track is minimum. The cost function is expressed as:
wherein t is f Representing the end time period of the time period,
representing the weight of the end aircraft, the superscript (1) indicates the climb segment. Given the boundary conditions and constraints, the minimum track dynamic pressure limit is 10kPa and the maximum track dynamic pressure limit is 75kPa. Initial mass m of aircraft 0 Climbing terminal mass m f Depending on the different schemes.
And finally, outputting an influence rule of the call of the comprehensive energy system based on the optimal track on the overall performance of the combined power according to the optimal result, and finishing the evaluation of the comprehensive energy system based on the flight/emission cooperative control strategy.
Claims (4)
1. The comprehensive energy system evaluation method based on the fly/send cooperative control strategy is characterized by comprising the following steps of:
1) Parameter initialization: setting target required power and initial conditions, dividing a flight phase into segmentation points by combining the characteristics of a combined engine, setting constraint conditions and control quantity, and giving a reasonable initial parameter range;
2) Establishing an aircraft dynamics model: considering the track characteristic influence of a vertical plane climbing section, regarding the aircraft as a particle model moving on a vertical plane, simplifying a six-degree-of-freedom model of the aircraft according to requirements, and establishing a state differential equation of each state parameter;
3) Establishing a combined engine model: under certain flight working conditions, a dynamic model of a typical TBCC engine is established, and finally, the attack angle change rate and a TBCC throttle lever are used as control quantities to be combined with an aircraft dynamic model;
4) Building a comprehensive energy system model: three energy extraction modes are established for the flight speed domains of Ma 0-7 so as to be applicable to different working speed domains; if the value of Ma is more than 0 and less than or equal to 2, adopting a power generation mode of extracting shaft work by a high-pressure shaft of the turbine engine; if 2< Ma is less than or equal to 5, air is led out from the outlet section of the air inlet channel to drive the air turbine to generate electricity; if the Ma is more than 5 and less than or equal to 7, leading out air from the section of the outlet of the air inlet channel, and then burning the air in the power generation combustion chamber to drive the turbine to generate power;
5) Solving an optimal track: solving an optimal flight path of the aircraft based on a Gaussian pseudo-spectrum method, setting the flight altitude, the speed, the climbing angle, the aircraft quality and the attack angle as state parameters by combining the model, setting the attack angle change rate and a TBCC throttle lever as control amounts, expressing the optimization problem of the climbing path as corresponding cost functions and parameter limits, and taking the minimum fuel consumption as a performance index; and outputting an influence rule of the call of the comprehensive energy system based on the optimal track on the overall performance of the combined power according to the optimal result, and finishing the evaluation of the comprehensive energy system based on the flight/emission cooperative control strategy.
2. The method for evaluating an integrated energy system based on a cooperative control strategy of flight/hair as claimed in claim 1, wherein in step 1), said setting target required power and initial conditions including flight altitude and mach; the segmentation points are set to be Ma2 and Ma5.
3. The comprehensive energy system evaluation method based on the cooperative control strategy of the flying/sending system as claimed in claim 1, wherein in the step 3), the specific steps of establishing the combined engine model are as follows:
(1) Establishing a combined engine air inlet channel model:
selecting an axisymmetric air inlet, and calculating performance parameters such as a total pressure recovery coefficient, a flow capture coefficient, a resistance coefficient and the like of the model according to given inlet conditions and air inlet design parameters to obtain outlet parameters of the air inlet;
(2) Establishing a turbine engine working model:
calculating the air flow parameters of each section of the engine and the performance parameters such as unit thrust, fuel consumption rate, specific impulse and the like of the engine through working process parameters, and calculating the thrust of the turbine engine by combining the captured air flow;
(3) Establishing a working model of the ramjet engine:
the thrust and specific impulse of the engine are calculated through the thrust and specific impulse characteristics of the unit flow, only the Mach number effect is considered, the height and the throttling characteristics are not considered, and the unit flow thrust and the specific impulse can be obtained through modeling according to a known change rule.
4. The method for evaluating a comprehensive energy system based on a cooperative control strategy of claim 1, wherein in step 4), the comprehensive energy system model is established as follows:
(1) Turbine shaft work extraction model: a certain required power is extracted from a high-pressure shaft of the turbine engine, and a motor is driven to generate electricity through a transmission device;
(2) Air turbine power generation model: on the basis of total temperature, total pressure and flow of incoming flow at the outlet of the air inlet channel, introducing a turbine working model to reversely solve the required target power to obtain the flow of air to be led, and iteratively calculating the influence of the air-led on the overall performance of the current combined ramjet engine;
(3) Gas turbine power generation model: and (3) leading out gas at the outlet of the air inlet channel, burning the gas through a combustion chamber, introducing a turbine working model to reversely solve the required target power on the basis of the total temperature, the total pressure and the flow of the gas to obtain the flow of the gas to be led, limiting the total temperature of the outlet by 2200K, and then iteratively calculating the influence of the gas to the overall performance of the current ramjet engine.
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