Rotary detonation engine pressure signal construction method and device

Abstract

The invention discloses a pressure signal construction method for a rotary detonation engine. The method comprises the steps that 1, based on a thermodynamic model of the rotary detonation engine, static pressure distribution parameters of the rotary detonation engine under the given flight condition and the controlled quantity input condition are obtained in an iterative solution mode; 2, calculating the change condition of the pressure value p of any pressure measuring point in the rotary detonation combustion chamber along with time t in a signal updating period delta t required by one-time calculation of the thermodynamic model; and step 3, constructing a pressure signal of each section in the signal updating period delta t. The invention further discloses a rotary detonation engine pressure signal construction device. According to the invention, pressure signals and change trends of all sections of the rotating detonation engine in a cross-space and wide-speed-domain range can be simulated, especially time-varying characteristics of periodic pressure distribution signals of the rotating detonation combustion chamber, and simulation and test requirements of development of a rotating detonation engine control system are met.

Description

Technical Field

[0001] The invention relates to a method for constructing an aero-engine pressure signal, in particular to a method for constructing a rotating detonation engine pressure signal, and belongs to the technical field of aero-engine simulation. Background Art

[0002] With the development of modern aviation technology, people have higher and higher requirements for the performance of aircraft engines. Traditional aircraft engines use the Brayton cycle, which continuously performs isobaric combustion in the combustion chamber, and the cycle thermal efficiency is relatively limited. Detonation combustion combines the combustion wave with the shock wave. Compared with the former, the pressure increases sharply after the detonation wave, which can produce higher thermal efficiency. Therefore, detonation engines based on the approximate Rankine cycle are becoming the mainstream of research at home and abroad.

[0003] As the most advanced detonation combustion technology, rotating detonation proposes a safer and more efficient design scheme for applying detonation combustion to the engine combustion chamber. The rotating detonation engine can continue to detonate after a single detonation, has high thermal efficiency and a relatively simple structure. It can effectively broaden the lower limit of the working Mach number of traditional subsonic ramjet engines, and still has the possibility of maintaining rotating detonation combustion under hypersonic flight conditions. It is a high-speed, supersonic flight aircraft engine with great potential. For traditional turbofan and turbojet engines, the original combustion chamber can be replaced with a rotating detonation combustion chamber, or in the form of additional series-parallel rotating detonation combustion chambers, so as to apply the rotating detonation combustion technology to form a turbine-based rotating detonation engine.

[0004] The high-frequency, periodic fluctuations in the combustion chamber pressure of this type of rotating detonation engine are the key indicator for monitoring whether it is in a rotating detonation combustion state. For aerospace engines, their flight envelope has the characteristics of crossing speed domains and crossing space. In order to ensure that the engine can operate safely and stably within the entire envelope, the control system will achieve full process control of the engine through various control algorithms, which includes monitoring and feedback control of the key characteristics of rotating detonation combustion.

[0005] The current engineering development of rotating detonation engines is in its infancy, and there is no effective platform or technology for testing and verifying control systems developed for rotating detonation engines. In addition, engine testing is costly and has a long development cycle, which makes it difficult to meet the development needs of control systems that require testing-rapid iteration-testing in the early stages of development. Therefore, it is not conducive to the development of controller systems. Therefore, there is an urgent need for a method that can simulate the pressure signal of a rotating detonation engine within the full envelope and is oriented to control application requirements, so as to provide key signal characteristics and change trends of rotating detonation engines within the safety envelope to provide support for the development and verification of control systems.

[0006] The existing thermodynamic model of rotating detonation engine can output the thermodynamic parameters of each section after each dynamic calculation, and then effectively measure the discrete pressure signal of each section during the whole model control simulation process. Except for the rotating detonation combustion chamber, there are relatively mature 0-dimensional component-level modeling methods for all components of the engine. Its characteristics are that the thermodynamic parameters on the same section are consistent. Therefore, the real-time pressure calculated by the model can be output as the dynamic pressure signal of the entire section. The pressure of the rotating detonation combustion chamber is distributed in two dimensions. According to the pressure distribution characteristics of the combustion chamber, the pressure at different measuring points on the same section will vary significantly according to the position of the detonation wave: the pressure at the wave surface of the detonation wave is the highest, and the pressure increases sharply when the incoming flow passes through the wave surface; the pressure at the end of the blockage area is the lowest and is equal to the incoming flow pressure. The detonation wave propagates rapidly along the annular combustion chamber, and the pressure at a certain point on the combustion chamber wall also changes continuously, reflecting the time-varying characteristics of periodic surges and dips. The existing rotating detonation combustion chamber model can only output the static pressure distribution of the detonation wave at the current sampling moment, lacks the ability to directly output the pressure at a fixed point in the combustion chamber, and cannot measure the dynamic pressure signal of a fixed point in the detonation combustion chamber in real time to meet the needs of controller feedback control. Therefore, the traditional method of directly feeding back the pressure signal through the model calculation results cannot be directly applied to the rotating detonation engine. Summary of the invention

[0007] The technical problem to be solved by the present invention is to overcome the shortcomings of the existing technology and provide a method for constructing a pressure signal of a rotating detonation engine, which can simulate the pressure signals and changing trends of each section of the rotating detonation engine across space and a wide speed range, especially the time-varying characteristics of the periodic pressure distribution signal of the rotating detonation combustion chamber, to meet the simulation and experimental needs of the development of a rotating detonation engine control system.

[0008] The present invention specifically adopts the following technical solutions to solve the above technical problems:

[0009] A method for constructing a pressure signal of a rotating detonation engine comprises the following steps:

[0010] Step 1, based on the rotating detonation engine thermodynamic model, obtain the static pressure distribution parameters of the rotating detonation engine under given flight conditions and control variable input by iterative solution, including the pressure distribution p(r) in the rotating detonation combustion chamber with the detonation wave head as the starting point;

[0011] Step 2: Calculate the change of the pressure value p of any pressure measuring point in the rotating detonation combustion chamber over time t within the signal update period Δt required for one calculation of the thermodynamic model according to the following formula:

[0012]

[0013] Among them, the wave head position L and the initial wave head position L0 are respectively the current and initial circumferential distances of the detonation wave head relative to the measuring point along the propagation direction of the detonation wave, v d is the detonation wave velocity, C is the circumference of the rotating detonation combustion chamber, t d is the detonation wave period, l is the number of complete detonation wave periods within a signal update period Δt;

[0014] Step 3: Construct the pressure signal of each cross section within the signal update period Δt:

[0015] For each cross section of the non-rotating detonation combustion chamber, the pressure signal is constructed according to the following formula:

[0016] p out =p(qΔt s )@p z ,0≤qΔt s <Δt,q=0,1,2,...

[0017] For each cross section in the rotating detonation combustion chamber, the pressure signal is constructed according to the following formula:

[0018]

[0019] Among them, Δt s is the signal sampling period, and z represents the section number.

[0020] Preferably, the detonation wave head height h and the blockage ratio B are taken as guess values, and the pressure distribution p(r) with the detonation wave head as the starting point in the rotating detonation combustion chamber under given flight conditions and control variable input is obtained by iterative solution.

[0021] Based on the same inventive concept, the following technical solutions can also be obtained:

[0022] A rotating detonation engine pressure signal construction device, comprising:

[0023] Thermodynamic model calculation module, used to obtain the static pressure distribution parameters of the rotating detonation engine under given flight conditions and control input by iterative solution based on the rotating detonation engine thermodynamic model, including the pressure distribution p(r) in the rotating detonation combustion chamber with the detonation wave head as the starting point;

[0024] The rotating detonation combustion chamber pressure calculation module is used to calculate the change of the pressure value p of any pressure measuring point in the rotating detonation combustion chamber with time t within the signal update period Δt required for one calculation of the thermodynamic model according to the following formula:

[0025]

[0026] Among them, the wave head position L and the initial wave head position L0 are respectively the current and initial circumferential distances of the detonation wave head relative to the measuring point along the propagation direction of the detonation wave, v d is the detonation wave velocity, C is the circumference of the rotating detonation combustion chamber, t d is the detonation wave period, l is the number of complete detonation wave periods within a signal update period Δt;

[0027] The pressure signal construction module is used to construct the pressure signal of each cross section within the signal update period Δt:

[0028] For each cross section of the non-rotating detonation combustion chamber, the pressure signal is constructed according to the following formula:

[0029] p out =p(qΔt s )@p z ,0≤qΔt s <Δt,q=0,1,2,...

[0030] For each cross section in the rotating detonation combustion chamber, the pressure signal is constructed according to the following formula:

[0031]

[0032] Among them, Δt s is the signal sampling period, and z represents the section number.

[0033] Preferably, the thermodynamic model of the rotating detonation engine uses the detonation wave head height h and the blockage ratio B as guess values, and obtains the pressure distribution p(r) in the rotating detonation combustion chamber with the detonation wave head as the starting point under given flight conditions and control variable inputs through an iterative solution.

[0034] Compared with the prior art, the technical solution of the present invention has the following beneficial effects:

[0035] (1) High applicability: The present invention can calculate the pressure of each cross section of a rotating detonation engine within a wide speed range and a large flight envelope across space, and can meet the signal construction requirements of rotating detonation engine control simulation for current control applications.

[0036] (2) High confidence and simple calculation: The construction of the pressure signal of the present invention is based on the aerodynamic thermodynamics theory of the rotating detonation engine, the engine working principle, etc., combined with the essential principles and working characteristics of the rotating detonation combustion chamber, thereby ensuring the high confidence of the calculated pressure signal value, and being able to calculate the pressure change at the corresponding position in each model update cycle according to the measuring point position as the dynamic pressure signal output of the measuring point; the pressure signal acquisition of the present invention is completely based on the model, and there is no need to perform numerical calculations such as CFD, which greatly reduces the amount of calculation for generating the pressure signal, improves the real-time performance of the calculation, and reduces the difficulty of the calculation.

[0037] (3) Versatility and portability: The present invention is implemented based on component-level modeling and signal construction based on model calculation results, and is applicable to ramjet engines, turbojets, turbofans, turboshafts, turboprops, variable cycle engines, and combined cycle engines with rotating detonation combustion chambers. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] Figure 1 This is the structural diagram of the rotating detonation ramjet engine;

[0039] Figure 2 A flow chart for constructing a pressure signal of a rotating detonation engine of the present invention;

[0040] Figure 3 This is a schematic diagram of the location of the pressure measurement points in the rotating detonation combustion chamber;

[0041] Figure 4 is the pressure diagram of the measuring point under signal generation condition 1; (a), (b), and (c) are the pressure P of the measuring point within a unit detonation wave cycle, respectively. d , the pressure at the measuring point within the signal update cycle P, the pressure signal P at the measuring point of the combustion chamber inlet section out ;

[0042] Figure 5 is the pressure diagram of the measuring point under signal generation condition 2; (a), (b), and (c) are the pressure P of the measuring point within a unit detonation wave cycle, respectively. d , the pressure at the measuring point within the signal update cycle P, the pressure signal P at the measuring point of the combustion chamber inlet section out ;

[0043] Figure 6 is the pressure diagram of the measuring point under signal generation condition 3; (a), (b), and (c) are the pressure P of the measuring point within a unit detonation wave cycle, respectively. d , the pressure at the measuring point within the signal update cycle P, the pressure signal P at the measuring point of the combustion chamber inlet section out . DETAILED DESCRIPTION

[0044] In view of the fact that the existing technology cannot meet the needs of pressure measurement signal construction and feedback of the controlled object required for the development of rotating detonation engine control system, the present invention is based on the principles of aerodynamic thermodynamics, aeroengine principles, rotor dynamics, etc., to establish aerodynamic thermodynamic models of each component, and calculate the distribution of pressure parameters of each section according to flight conditions and engine control input, especially the two-dimensional distribution and dynamic change law of combustion chamber pressure, and further generate real sensor signals through a signal simulation device. The applicable simulation object is an aerospace engine that includes a rotating detonation combustion chamber and is composed of multiple components and works together to complete a thermodynamic cycle, including but not limited to turbojet engines, turbofan engines, turboshaft engines, turboprop engines, variable cycle engines, ramjet engines, combined cycle engines, etc.

[0045] In order to facilitate public understanding, the technical solution of the present invention is described in detail below by taking a rotating detonation ramjet engine as an example.

[0046] Figure 1 It is a schematic diagram of the structure of a rotating detonation ramjet engine; in the figure, section 0 is the far front flow, section 1 is the inlet inlet, section 2 is the inlet outlet, section 3 is the isolation section outlet and the rotating detonation combustion chamber inlet, section 4 is the rotating detonation combustion chamber outlet, section 8 is the tail nozzle throat section, and section 9 is the tail nozzle outlet.

[0047] The pressure signal construction process of the rotating detonation ramjet engine is as follows: Figure 2 As shown, the specific steps include:

[0048] Step 1, based on the rotating detonation engine thermodynamic model, obtain the static pressure distribution parameters of the rotating detonation engine under given flight conditions and control variable input by iterative solution, including the pressure distribution p(r) in the rotating detonation combustion chamber with the detonation wave head as the starting point;

[0049] The structure of the rotating detonation ramjet engine studied in this embodiment mainly includes four major components: an air inlet, an isolation section, a rotating detonation combustion chamber, and a tail nozzle, so these four major components need to be modeled. In particular, since the object of this application embodiment has no rotor component, the rotor dynamics modeling is not given in this embodiment, but for a rotating detonation engine (turbine-based engine) with a rotor component, it is also necessary to calculate the speed change law through rotor dynamics modeling.

[0050] The three major components of the inlet duct, isolation section and tail nozzle are established according to the conventional component-level modeling method, which will not be repeated here. For the rotating detonation combustion chamber, a two-dimensional combustion chamber model is established here based on the CJ theory. In fact, the method for constructing the combustion chamber model can also be constructed using the existing HJ theory, ZND theory, etc., and is not limited to the CJ theory.

[0051] (1) Calculation of detonation wave velocity v based on CJ theory d

[0052] v d =f(k CJ ,R CJ ,c p,3 ,c p,CJ ,T3,P3,v3,f3,H f ,η g ) (1)

[0053] In the formula, k represents the specific heat ratio, R is the gas constant, c p is the constant pressure specific heat capacity, T3 represents the static temperature at the combustion chamber inlet, P3 represents the static pressure at the combustion chamber inlet, v3 represents the flow rate at the combustion chamber inlet, f3 represents the fuel consumption rate of the combustion chamber, H f Indicates the calorific value of fuel oil, η g represents combustion efficiency, subscript CJ represents parameters under CJ theory, and subscript 3 represents section 3, i.e., the inlet section of the detonation combustion chamber.

[0054] (2) Calculate the shock wave angle β for the calculation of parameters after the detonation wave expands:

[0055] β=f(k CJ ,Ma d ) (2)

[0056] In the formula, Ma d Represents the Mach number of the airflow after passing through the detonation wave.

[0057] (3) Calculate the detonation wave pressure distribution p in the annular combustion chamber based on the shock wave angle β and the detonation wave head height h bz (r):

[0058] p bz (r) = f(k CJ ,P CJ ,C,r,h,sinβ) (3)

[0059] Where P CJ is the pressure after the detonation wave under the CJ theory, which is calculated according to the CJ theory and will not be repeated here. C is the circumference of the combustion chamber, r is the position on the circumference relative to the detonation wave head, r∈[0,B*C], and B is the intake blockage ratio. The static pressure of the non-blocked part of the detonation combustion chamber is equal to the static pressure at the inlet of the detonation combustion chamber. Combined with the detonation wave pressure distribution, the overall pressure distribution p(r) of the rotating detonation combustion chamber with the detonation wave head as the starting point and the pressure gradually decreasing until the flow pressure is obtained:

[0060]

[0061] The common working equations are set according to the working characteristics of the engine: Since there is no rotor component in this embodiment, the power balance common working equation is not set. In combination with the working characteristics of the four components of the rotating detonation ramjet engine, two common working equations of flow balance and static pressure balance are set at the inlet of the combustion chamber:

[0062] (1) According to the gas flow balance entering the combustion chamber, set

[0063]

[0064] Where, W3 is the actual gas flow rate at the inlet of the detonation combustion chamber, which can be calculated based on the blockage ratio; W d is the flow rate after the detonation wave.

[0065] (2) According to the static pressure balance of the combustion chamber inlet, set

[0066]

[0067] The detonation wave head height h and the blockage ratio B are selected as guess values ​​for iterative calculation.

[0068] Based on the above steps, a complete rotating detonation ramjet engine thermodynamic model including the air inlet, isolation section, rotating detonation combustion chamber, and tail nozzle components can be established.

[0069] By iteratively solving the thermodynamic model, the specific value of the pressure signal to be constructed can be obtained, which is used for the subsequent signal generator to generate a signal. The iterative solution of the above thermodynamic model can adopt various existing iterative algorithms such as Newton's method and quasi-Newton's method. The following is a brief description of the Newton-Raphson method as an example:

[0070] (1) Initializing the established rotating detonation ramjet engine thermodynamic model and initializing the initial guess values ​​of the detonation wave head h and the blockage ratio B;

[0071] (2) Given the current flight conditions and control variable input; in this embodiment, the flight conditions include the altitude H and the Mach number Ma, and the control variable input is the fuel flow m fb ;

[0072] (3) Use the Newton-Raphson method to iteratively solve:

[0073] X=XJ -1 E (7)

[0074] Where, X = [h B] T , E=[e1 e2] T , J is the Jacobian matrix of E with respect to X;

[0075] Iterate the system of co-working equations until the residual e of each co-working equation is less than 10 -6 , thereby obtaining the solution of the equation group, that is, the accurate detonation wave height h and blockage ratio B. The detonation wave head height h and blockage ratio B are brought into the established thermodynamic model to calculate the temperature and pressure values ​​of each cross section and the static pressure distribution at the inlet of the rotating detonation combustion chamber.

[0076] (4) Rotor dynamics calculation: Since the object of this embodiment is a ramjet engine without a rotor component, rotor dynamics calculation is not performed. Instead, it is directly determined whether the dynamic calculation process is completed.

[0077] Step 2: Calculate the change of the pressure value p at any pressure measuring point in the rotating detonation combustion chamber over time t within the signal update period Δt required for one calculation of the thermodynamic model:

[0078] Assuming that continuous dynamic, multi-cycle signal construction is performed, the signal update cycle is consistent with the control cycle of a typical engine control system to meet the signal acquisition and feedback requirements of the control system. In this embodiment, the update cycle Δt is set to 20ms. In particular, it is pointed out that the signal update cycle referred to here is the sampling step length for updating each thermal parameter of the engine after the model is calculated once, rather than the update cycle of the signal generation system's external output signal (the update cycle of the signal generation system's external output signal can be as short as microseconds or even nanoseconds, depending on the actual signal construction needs and the signal generation capability of the signal generation system itself). It is worth noting that when the corresponding control system control cycle is selected as a smaller value, the signal update cycle of the present invention can be synchronously reduced to meet the actual control system's signal acquisition and feedback requirements.

[0079] First calculate the current position L of the detonation wave head:

[0080]

[0081] L=mod(s,C) (9)

[0082] Where s represents the distance traveled by the detonation wave, Δt represents the signal update period, N represents that a total of N signal update periods have been calculated up to the current time, L0 represents the initial wave head position, that is, the detonation wave initiation position, and mod represents the remainder operation; note that the wave head position L and L0 here are the circumferential distances of the detonation wave head relative to the measuring point along the propagation direction of the detonation wave.

[0083] Assuming that the pressure distribution p(r) of the rotating detonation combustion chamber with the detonation wave head as the starting point is obtained after iterative solution, the initial pressure value p(L) of the pressure measurement point is obtained according to the pressure distribution; at the same time, the detonation wave frequency f is calculated according to the detonation wave velocity re , detonation wave period t d :

[0084]

[0085] Therefore, in each detonation wave period t d During this time, the pressure value at the pressure measuring point is

[0086]

[0087] Therefore, in one signal update cycle, there are l complete detonation wave cycles

[0088]

[0089] In the formula, ceil means rounding down.

[0090] Then in one signal update cycle, the pressure value curve of the pressure measuring point is:

[0091]

[0092] Step 3: Construct the pressure signal of each cross section within the signal update period Δt:

[0093] Assuming that the signal generation system outputs the pressure signal at a specific sampling rate S, the signal sampling period Δt s for

[0094]

[0095] Special note on the difference between the signal update period and the signal sampling period: the signal update period refers to the time to maintain the pressure distribution law unchanged, and the signal sampling period refers to the period in which the signal generating system outputs pressure once at the sampling rate S.

[0096] Therefore, for the cross-sectional pressure of the non-combustion chamber, the pressure signal can be considered to be consistent with the model output pressure; the signal generation system constructs the pressure signal within the signal update period according to formula (16):

[0097] p out =p(qΔt s )@p z ,0≤qΔt s <Δt,q=0,1,2,... (16)

[0098] Where z represents the section number.

[0099] For any cross section in the rotating detonation combustion chamber, the signal generation system constructs the pressure signal within the signal update period according to formula (17):

[0100]

[0101] In order to demonstrate the effect of the technical solution of the present invention, the pressure signal is continuously generated under different engine sizes, flight conditions and control input conditions. The following results take the pressure signal of the rotating detonation combustion chamber as an example, and the signal update period is 20ms. Without loss of generality, it is assumed that the combustion chamber pressure measurement point is located at the combustion chamber entrance at 0° of the circumference, such as Figure 3 Table 1 shows different signal generation conditions. Table 2 shows the characteristic parameters of the detonation wave under different signal conditions.

[0102] Table 1 Signal generation conditions

[0103]

[0104] Table 2 Detonation wave characteristic parameters

[0105]

[0106] Figures 4 to 6 The pressure P of the measuring point within a unit detonation wave period under the above three signal generation conditions are given respectively. d , the pressure at the measuring point within the signal update cycle P, the pressure signal P at the measuring point of the combustion chamber inlet section out Among them, the pressure P d ,P,P out As can be seen from the figure, the present invention can effectively simulate the pressure of the rotating detonation combustion chamber and has the ability to continuously output the pressure signals of each section of the rotating detonation ramjet engine for controlling the simulation.

Claims

1. A method for constructing a pressure signal of a rotating detonation engine, characterized in that: The following steps are involved: Step 1, based on the rotating detonation engine thermodynamic model, obtain the static pressure distribution parameters of the rotating detonation engine under given flight conditions and control variable input by iterative solution, including the pressure distribution p(r) in the rotating detonation combustion chamber with the detonation wave head as the starting point; Step 2: Calculate the change of the pressure value p of any pressure measuring point in the rotating detonation combustion chamber over time t within the signal update period Δt required for one calculation of the thermodynamic model according to the following formula: Among them, the wave head position L and the initial wave head position L0 are respectively the current and initial circumferential distances of the detonation wave head relative to the measuring point along the propagation direction of the detonation wave, v d is the detonation wave velocity, C is the circumference of the rotating detonation combustion chamber, t d is the detonation wave period, l is the number of complete detonation wave periods within a signal update period Δt; Step 3: Construct the pressure signal of each cross section within the signal update period Δt: For each cross section of the non-rotating detonation combustion chamber, the pressure signal is constructed according to the following formula: p out =p(qΔt s )@p z ,0≤qΔt s <Δt,q=0,1,2,... For each cross section in the rotating detonation combustion chamber, the pressure signal is constructed according to the following formula: Among them, Δt s is the signal sampling period, and z represents the section number.

2. The method for constructing a pressure signal of a rotating detonation engine according to claim 1, characterized in that: Taking the detonation head height h and the blockage ratio B as guess values, the pressure distribution p(r) with the detonation head as the starting point in the rotating detonation combustion chamber under given flight conditions and control variable input is obtained through iterative solution.

3. A rotating detonation engine pressure signal construction device, characterized in that: include: Thermodynamic model calculation module, used to obtain the static pressure distribution parameters of the rotating detonation engine under given flight conditions and control input by iterative solution based on the rotating detonation engine thermodynamic model, including the pressure distribution p(r) in the rotating detonation combustion chamber with the detonation wave head as the starting point; The rotating detonation combustion chamber pressure calculation module is used to calculate the change of the pressure value p of any pressure measuring point in the rotating detonation combustion chamber with time t within the signal update period Δt required for one calculation of the thermodynamic model according to the following formula: Among them, the wave head position L and the initial wave head position L0 are respectively the current and initial circumferential distances of the detonation wave head relative to the measuring point along the propagation direction of the detonation wave, v d is the detonation wave velocity, C is the circumference of the rotating detonation combustion chamber, t d is the detonation wave period, l is the number of complete detonation wave periods within a signal update period Δt; The pressure signal construction module is used to construct the pressure signal of each cross section within the signal update period Δt: For each cross section of the non-rotating detonation combustion chamber, the pressure signal is constructed according to the following formula: p out =p(qΔt s )@p z ,0≤qΔt s <Δt,q=0,1,2,... For each cross section in the rotating detonation combustion chamber, the pressure signal is constructed according to the following formula: Among them, Δt s is the signal sampling period, and z represents the section number.

4. The rotating detonation engine pressure signal construction device according to claim 3, characterized in that: The thermodynamic model of the rotating detonation engine takes the detonation head height h and the blockage ratio B as guess values, and obtains the pressure distribution p(r) in the rotating detonation combustion chamber with the detonation head as the starting point under given flight conditions and control variable input through iterative solution.

Images