[1] YAN C J, FAN W. Principles and key technologies of pulse detonation engine(2005).

[2] WANG B, XIE Q F, WEN H C et al. Research progress of detonation engines. Journal of Propulsion Technology, 42, 721-737(2021).

[3] ZHENG L X, WANG Z W, HUANG X Q et al. Pulse detonation turbine engine technology(2019).

[4] PEACE J T, LU F K. Detonation⁃to⁃shock wave transmission at a contact discontinuity. Shock Waves, 28, 981-992(2018).

[5] BIRMAN V. Thermal effects on measurements of dynamic processes in composite structures using piezoelectric sensors. Smart Materials and Structures 5.4, 5, 379-385(1996).

[6] GRAY J A T. Reduction in the run⁃up distance for the deflagration⁃to⁃detonation transition and applications to pulse detonation combustion(2018).

[7] BARLIAN A A, PARK W T, MALLON J R et al. Review： semiconductor piezoresistance for microsystems. Proceedings of the IEEE, 97, 513-552(2009).

[8] CARTER S, CHIVERS J et al. Selecting piezoresistive vs. piezoelectric pressure transducers. Kulite Semiconductor Products, 1-25(2016).

[9] SETTLES G. Schlieren and shadowgraph techniques： visualizing phenomena in transparent media. Applied Mechanics Reviews, 55, 76-77(2022).

[10] HARGATHER M J, SETTLES G S. A comparison of three quantitative schlieren techniques. Optics & Lasers in Engineering, 50, 8-17(2012).

[11] ALLGOOD D, GUTMARK E, MEYER T et al. Computational and experimental studies of pulse detonation engines(2003).

[12] ELSINGA G E, OUDHEUSDEN B W, SCARANO F et al. Assessment and application of quantitative schlieren methods： calibrated color schlieren and background oriented schlieren. Experiments in Fluids, 36, 309-325(2004).

[13] GLASER A, CALDWELL N, GUTMARK E. Performance measurements of a pulse detonation combustor array integrated with an axial flow turbine(2006).

[14] OWENS Z C. Flowfield characterization and model development in detonation tubes(2008).

[15] OPALSKI A, PAXSON D, WERNET M. Detonation driven ejector exhaust flow characterization using planar DPIV, 1-20(2005).

[16] HAGHDOOST M R, EDGINGTON⁃MITCHELL D M, PASCHEREIT C O et al. Investigation of the exhaust flow of a pulse detonation combustor at different operating conditions based on high⁃speed schlieren and PIV, 1512-1537(2019).

[17] HAGHDOOST M R, EDGINGTON⁃MITCHELL D, PASCHEREIT C O et al. High⁃speed schlieren and particle image velocimetry of the exhaust flow of a pulse detonation combustor. AIAA Journal, 58, 3527-3543(2020).

[18] REZAY HAGHDOOST M, EDGINGTON⁃MITCHELL D, NADOLSKI M et al. Dynamic evolution of a transient supersonic trailing jet induced by a strong incident shock wave. Physical Review Fluids, 5(2020).

[19] LIU P J, WANG Z X, YANG B et al. Research on gas velocity measurement method combining absorption spectroscopy and cross⁃correlation method. Spectroscopy and Spectral Analysis, 37, 532-536(2017).

[20] MATTISON D W, BROPHY C M, SANDERS S T et al. Pulse detonation engine characterization and control using tunable diode⁃laser sensors. Journal of Propulsion and Power, 19, 568-572(2003).

[21] LYLE K T, JEFFRIES J B, HANSON R K. Diode⁃laser sensor for air⁃mass flux 1： design and wind⁃tunnel validation. AIAA Journal, 45, 2204-2212(2007).

[22] ROUSER K P, KING P I, SCHAUE F R et al. Time⁃accurate flow field and rotor speed measurements of a pulsed detonation driven turbine, 7749-7764(2011).

[23] BONG C, LEE J W, SUN H J et al. TDLAS measurements of temperature and water vapor concentration in a flameless MILD combustor. Measurement Science and Technology, 32(2021).

[24] MUNDAY D, GEORGE A S, DRISCOLL R et al. The design and validation of a pulse detonation engine facility with and without axial turbine integration(2013).

[25] GEORGE A C S, DRISCOLL R, MUNDAY D E et al. Experimental comparison of axial turbine performance under pulsed⁃air and pulsed⁃detonation flows(2013).

[26] AMBADY S, HOFER D C, TANGIRALA V E et al. Turbine efficiency for unsteady， periodic flows. Journal of Turbomachinery, 134, 1-6(2012).

[27] XIONG C. Optical diagnostics and intake / exhaust system research of APDE(2009).

[28] HUANG X Q, YAN C J, FAN W et al. Exploratory experimental study on the combustion efficiency of pulse detonation. Journal of Aerospace Power, 962-966(2006).

[29] JENKINS T P, HANSON R K. A soot temperature diagnostic combining flame emission and modulated laser absorption(2000).

[30] JENKINS T P, HANSON R K. Soot diagnostic for pulse detonation engine studies(2000).

[31] YANG S R, ZHAO J R et al. Multiplex CARS measurements in supersonic H2 / air combustion. Applied Physics B： Lasers and Optics, 68, 257-265(1999).

[32] MAGRE P, COLLIN G et al. Temperature measurements by CARS and intrusive probe in an air⁃hydrogen supersonic combustion. International Journal of Heat and Mass Transfer, 44, 4095-4105(2001).

[33] MAGRE P, BOUCHARDY P. Nitrogen and hydrogen coherent anti‐stokes raman scattering thermometry in a supersonic reactive mixing layer. Proceedings of the Combustion Institute, 28, 697-703(2000).

[34] CUTLER A D, MAGNOTTI G, CANTU L et al. Dual pump coherent anti‐stokes Raman spectroscopy measurements in a dual‐mode scramjet. Journal of Propulsion and Power, 30, 539-549(2014).

[35] CUTLER A D, GALLO E C A, CANTU L M L. Coherent anti‐Stokes Raman spectroscopy measurement of ethylene in combustion. Applied Optics, 56, 30-36(2017).

[36] KIM A, DEDIC C E, CUTLER A D. Development of a fs / ps CARS system for temperature and species measurements in a dual⁃mode scramjet combustor(2023).

[37] SPEARRIN R M, GOLDENSTEIN C S, SCHULTA I A et al. Simultaneous sensing of temperature， CO， and CO2 in a scramjet combustor using quantum cascade laser absorption spectroscopy. Applied Physics B, 117, 689-698(2014).

[38] BOECK L R, MÉVEL R, FIALA T et al. High⁃speed OH PLIF imaging of deflagration⁃to⁃detonation transition in H2⁃air mixtures. Experiments in Fluids, 57, 105-118(2016).

[39] BOECK L R, BERGER F M, HASSLBERGER J et al. Detonation propagation in hydrogen⁃air mixtures with transverse concentration gradients. Shock Waves, 26, 181-192(2016).

[40] YANG B, QI Z M, YANG H N et al. Velocity measurement method based on TDLAS for combustion flow. Journal of Combustion Science and Technology, 21, 516-520(2015).

[41] BONG C, LEE J, SUN H et al. TDLAS measurements of temperature and water vapor concentration in a flameless MILD combustor. Measurement Science and Technology, 32(2021).

[42] HARGATHER M J, SETTLES G S. A comparison of three quantitative schlieren techniques. Optics & Lasers in Engineering, 50, 8-17(2012).

[43] SANDERS S T, MATTISON D W, MA L et al. Wavelength agile diode⁃laser sensing strategies for monitoring gas properties in optically harsh flows： application in cesium⁃seeded pulse detonation. Optics Express, 10, 505-514(2002).

[44] ROUSER K P, KING P I, SCHAUER F R et al. Time resolved flow properties in a turbine driven by pulsed detonations. Journal of Propulsion and Power, 30, 1528-1536(2014).

[45] CHEN F, TAO B, HUANG B et al. Measurement of PDRE plume based on TDLAS technology. Journal of Combustion Science and Technology, 19, 501-506(2013).

[46] WU Z, LI J F, LU J et al. Temperature measurement of burning gas in pulse detonation engine based on TDLAS. Journal of Combustion Science and Technology, 30, 411-418(2024).

[47] ROUSER K P, KING P I, SCHAUER F R et al. Unsteady performance of a turbine driven by a pulse detonation engine, 13077-13092(2010).

[48] SURESH A, HOFER D C, TANGIRALA V E. Turbine efficiency for unsteady， periodic flows(2012).

[49] GLASER A, CALDWELL N, GUTMARK E. Performance of an axial flow turbine driven by multiple pulse detonation combustors(2007).

[50] CALDWELL N, GUTMARK E. Performance analysis of a hybrid pulse detonation combustor / gas turbine system, 3646-3655(2008).

[51] ROUSER K, KING P, SCHAUER F et al. Unsteady performance of a turbine driven by a pulse detonation engine(2010).

[52] HOFER D C, TANGIRALA V E, SURESH A. Turbine efficiency for unsteady， periodic flows. Journal of Turbomachinery(2012).

[53] GLASER A, CALDWELL N, GUTMARK E. Performance of an axial flow turbine driven by multiple pulse detonation combustors(2007).

[54] NICHOLLS J A, WILKINSON H R, MORRISON R B. Intermittent detonation as a thrust⁃producing mechanism. Journal of Jet Propulsion, 27, 534-541(1954).

[55] TAKEUCHI S, KASAHARA J et al. Net impulse measurements of pulse detonation tube by using fuel⁃air mixture(2010).

[56] KASAHARA J, ARAI T, MATSUO A. Net impulse measurements of pulse detonation tube by using fuel⁃air mixture. AIAA Paper(2003).

[57] COOPER M, JACKSON S, AUSTIN J et al. Direct experimental impulse measurements for detonations and deflagrations. Journal of Propulsion and Power, 18, 1033-1041(2002).

[58] COOPER M, SHEPHERD J E. Effect of porous thrust surfaces on detonation transition and detonation tube impulse. Journal of Propulsion and Power, 20, 811-819(2004).

[59] KIYANDA C B, TANGUAY V, HIGGINS A J et al. Effect of transient gas dynamic processes on the impulse of pulse detonation engines. Journal of Propulsion and Power, 18, 1124-1126(2002).

[60] HINKEY J B, BUSSING T R A, KAYE L. Shock tube experiments for the development of a hydrogen⁃fueled pulse detonation engine(1995).

[61] FAN W, YAN C J, HUANG X Q et al. Experimental investigation on two⁃phase pulse detonation engine. Combustion and Flame, 133, 441-450(2003).

[62] STANLEY S, BURGE K, WILSON D. Experimental investigation of pulse detonation wave phenomenon as related to propulsion application(1995).

[63] ZHANG F Y, FUJIWARA T, MIYASAKA T, al et. Detonation studies of high⁃frequency⁃operation pulse detonation engine with air / hydrogen, 1-7(2003).

[64] AARNIO M J, HINKEY J B, BUSSING T R A. Multiple cycle detonation experiments during the development of a pulse detonation engine(1996).

[65] HINKEY J, WILLIAMS J, HENDERSON S et al. Rotary⁃valved， multiple⁃cycle， pulse detonation engine experimental demonstration(1997).

[66] RASHEED A, TANGIRALA V E, PINARD P F et al. Experimental and numerical investigations of ejectors for PDE applications, 1-9(2003).

[67] SHEHADEH R, SARETTO S, LEE S Y et al. Thrust augmentation measurements for a pulse detonation engine driven ejector, 1-9(2004).

[68] WILSON J, SGONDEA A, PAXSON D E et al. Parametric investigation of thrust augmentation by ejectors on a pulsed detonation tube. Journal of Propulsion and Power, 23, 108-115(2007).

[69] ALLGOOD D, GUTMARK E, HOKE J et al. Performance measurements of multicycle pulse⁃detonation⁃engine exhaust nozzles. Journal of Propulsion and Power, 22, 70-77(2006).

[70] GLASER A, BRUMBERG J, RASHEED A et al. Investigations of thrust generated by a valved， multitube PDE with exit nozzles, 1-14(2008).

[71] KASAHARA J, HIRANO M, MATSUO A et al. Thrust measurement of a multicycle partially filled pulse detonation rocket engine. Journal of Propulsion and Power, 25, 1281-1290(2009).

[72] MATSUOKA K, ESUMI M, IKEGUCHI K B et al. Optical and thrust measurement of a pulse detonation combustor with a coaxial rotary valve. Combustion and Flame, 159, 1321-1338(2012).

[73] NGUYEN N, CUTLER A D. Pressure and thrust measurements of a high⁃frequency pulsed⁃detonation tube, 1930-1940(2008).

[74] HINKEY J, HENDERSON S, BUSSING T. Operation of a flight⁃scale rotary⁃valved， multiple⁃combustor， pulse detonation engine （RVMPDE）(1998).

[75] SCHAUER F, STUTRUD J, BRADLEY R. Detonation initiation studies and performance results for pulsed detonation engine applications(2001).

[76] KASAHARA J, HASEGAWA A, NEMOTO T et al. Thrust demonstration of a pulse detonation rocket "TODOROKI", 54-67(2007).

[77] TAKAGI S, MOROZUMI T, MATSUOKA K et al. Study on pulse detonation rocket engine using flight test demonstrator "TODOROKI II"(2014).

[78] LI J L, FAN W, CHEN W et al. Propulsive performance of a liquid kerosene / oxygen pulse detonation rocket engine. Experimental Thermal and Fluid Science, 35, 265-271(2011).

[79] STRONGE W J. Impact mechanics(2004).

[80] CARBONARO M. Aerodynamic force measurements in the VKI longshot hypersonic facility. New trends in instrumentation for hypersonic research, 317-325(1993).

[81] STORKMANN V, OLIVIER H, GRONIG H. Force measurements in hypersonic impulse facilities. AIAA Journal, 36, 342-348(1998).

[82] BERNSTEIN L P R C. Force Measurements in short⁃duration hypersonic facilities(1975).

[83] NAUMANN K W, ENDE H, MATHIEU G. Technique for aerodynamic force measurement within milliseconds in shock tunnel. Shock Waves, 1, 223-232(1991).

[84] TANNO H, KODERA M, KOMURO T et al. Aerodynamic force measurement on a large⁃scale model in a short duration test facility. Review of Scientific Instruments, 76(2005).

[85] TANNO H, KOMURO T, TAKAHASHI M et al. Unsteady force measurement technique in shock tubes. Review of Scientific Instruments, 75, 532-536(2004).

[86] MEE D J. Dynamic calibration of force balances for impulse hypersonic facilities. Shock Waves, 12, 443-455(2003).

[87] JOARDER R, JAGADEESH G. A new free floating accelerometer balance system for force measurements in shock tunnels. Shock Waves, 13, 409-412(2003).

[88] SANDERSON S R, SIMMONS J M. Drag balance for hypervelocity impulse facilities. AIAA Journal, 29, 2185-2191(1991).

[89] JOSHI M V, REDDY N M. Aerodynamic force measurements over missile configurations in IISc shock tunnel at M ∞=5.5. Experiments in Fluids, 4, 338-340(1986).

[90] SAHOO N, MAHAPATRA D R, JAGADEESH G et al. An accelerometer balance system for measurement of aerodynamic force coefficients over blunt bodies in a hypersonic shock tunnel. Measurement Science and Technology, 14, 260-272(2003).

[91] SATHEESH K, JAGADEESH G. Analysis of an internally mountable accelerometer balance system for use with non⁃isotropic models in shock tunnels. Measurements, 42, 856-862(2009).

[92] ROBINSON M, SCHRAMM J M, SCHRAMM K. An investigation into internal and external force balance configurations for short duration wind tunnels(2008).

[93] ROBINSON M J, MEE D J, PAULL A. Scramjet lift， thrust and pitching⁃moment characteristics measured in a shock tunnel. Journal of Propulsion and Power, 22, 85-95(2006).

[94] DANIEL W J T, MEE D J. Finite element modelling of a three⁃component force balance for hypersonic flows. Computers and Structures, 54, 35-48(1995).

[95] COOPER M, SHEPHERD J E. The effects of nozzles and extensions on detonation tube performance(2002).

[96] SMITH A L, MEE D J, DANIEL W J T et al. Design，modelling and analysis of a six component force balance for hypervelocity wind tunnel testing. Computers and Structures, 79, 1077-1088(2001).

[97] ABDEL⁃JAWAD M M, MEE D J, MORGAN R G. New calibration technique for multiple⁃component stress wave force balances. Review of Scientific Instruments, 78(2007).

[98] JOSHI D D. Unsteady thrust measurement techniques for pulse detonation engines(2014).

[99] JOSHI D D, LU F K. Unsteady thrust measurement for pulse detonation engines. Journal of Propulsion and Power, 32, 225-236(2016).