Dual pulse solid rocket engine barrier opening at different time state testing device and method

Abstract

A kind of double-pulse solid engine diaphragm opening different time state testing device and method.The device includes test container, two-pulse false medicine, two-pulse real medicine, heat insulation layer, sponge layer, one-pulse ignition top cover, two-pulse ignition device, diaphragm, transition section, nozzle;The inner wall of test container is sequentially bonded with heat insulation layer and sponge layer, two-pulse false medicine is placed on sponge layer, two-pulse real medicine is placed in two-pulse false medicine, the right side end surface of two-pulse false medicine and two-pulse real medicine and the inner hole surface of two-pulse real medicine are bonded with diaphragm;Transition section is fixed on test container at one end, and is fixedly connected with nozzle at the other end;Two-pulse ignition device is installed at the left end of test container, and one-pulse ignition top cover is installed on two-pulse ignition device.The present application can completely and truly reproduce the working state of two-pulse combustion chamber early stage of double-pulse engine, and further determine the state of diaphragm opening different time, which is helpful to improve the understanding of diaphragm opening process, and further improve the performance of engine.

Description

TECHNICAL FIELD

[0001] The application belongs to the field of double-pulse solid engine design, and relates to a testing device and method for different opening time states of an axial+radial isolation type double-pulse solid engine. BACKGROUND

[0002] The solid rocket engine has the advantages of simple structure, reliable operation, convenient use, good safety and low cost, but has the disadvantages of poor thrust controllability and lack of multiple starting capability, which affects the performance and development of the missile weapon system to some extent.

[0003] With the continuous emergence and development of new technologies, new materials and new processes, the missile weapon system has higher requirements for the solid rocket engine. In addition to the conventional requirements of high energy, high mass ratio and strong environmental adaptability, the engine is also required to have more flexible energy management capability. After years of efforts, major breakthroughs have been made in the core technologies of lightweight flexible soft partition, lightweight hard partition and multiple rapid response ignition. Therefore, the solid rocket multi-pulse engine has become an ideal energy management approach.

[0004] The multi-pulse solid rocket engine separates the propellant grain into several parts through an isolation device, and performs multiple shutdowns and startups. The missile can manage the engine energy output in real time according to the war requirements, and can reasonably adjust the thrust distribution and the interval time between pulses through the on-board program control, so that the missile can obtain flexible range adjustment, flight speed characteristics and multi-task capability, and can realize optimal control of the missile flight trajectory and optimal management of the engine energy, thereby comprehensively improving the comprehensive performance of various missile weapon systems.

[0005] The typical structure of the double-pulse solid rocket engine is: one pulse combustion chamber or propellant grain + one pulse ignition device + isolation device, two pulse combustion chambers or propellant grains + two pulse ignition devices + shared nozzle, wherein the isolation device can be axial, radial or axial+radial.

[0006] The working principle of the axial+radial partition type double-pulse solid rocket engine is as follows: after receiving the missile ignition instruction, the engine starts one pulse, and works for several seconds until the fuel is consumed and the engine is shut down, so that the missile is accelerated to the predetermined speed and enters the sustained flight. During the working period of the one pulse combustion chamber, the axial+radial partition must maintain structural integrity; after a certain interval, the two pulses are randomly controlled and started through the on-board program control, the combustion gas generated by the two pulse ignitions reversely opens the axial+radial partition, and the engine normally works for several seconds after the two pulse ignitions, and then the fuel is consumed again.

[0007] Through the working principle of axial + radial barrier type double pulse solid rocket engine, it can be found that whether the barrier can be normally opened according to the design established mode after receiving the double pulse ignition signal is directly related to whether the double pulse engine can normally work, especially in the first few seconds of the initial work of the double pulse combustion chamber. If the axial + radial barrier is not opened in the designed mode, too many fragments of the opened axial + radial barrier may cause the nozzle to be blocked, the pressure in the engine to be too high, and the engine to be blown up. Therefore, testing the state of the double pulse solid engine barrier at different times (especially in the initial ignition period) is of great significance to understanding the working mode of the barrier in the transient process of engine ignition.

[0008] At present, cold gas impact simulation test or numerical simulation is adopted in domestic and foreign documents to study the opening of the barrier, but these studies only aim at the ignition pressure of the engine and do not consider the situation after the double pulse combustion chamber is ignited, so they cannot fully represent the real situation of the double pulse combustion chamber in the first few seconds. SUMMARY

[0009] The technical problem solved by the present application is to overcome the shortcomings of the prior art and provide a double pulse solid engine barrier opening state testing device and method at different times.

[0010] The technical solution of the present application is:

[0011] The double pulse solid engine barrier opening state testing device at different times comprises a test container, a double pulse false propellant, a double pulse true propellant, an adiabatic layer, a sponge layer, a one-pulse ignition top cover, a double pulse ignition device, a barrier, a transition section and a nozzle.

[0012] The inner wall of the test container is sequentially bonded with the adiabatic layer and the sponge layer, the double pulse false propellant is placed on the sponge layer, the double pulse true propellant is placed in the columnar hollow structure of the double pulse false propellant, and the right end surface of the double pulse false propellant and the double pulse true propellant and the inner hole surface of the double pulse true propellant are bonded with the barrier; one end of the transition section is fixed on the test container by bolts, the transition section and the test container press the barrier, and the other end of the transition section is fixedly connected with the nozzle.

[0013] The double pulse ignition device is installed on the left end of the test container by bolts, two through holes are formed in the double pulse ignition device, one of the through holes is communicated with the double pulse true propellant for igniting the double pulse true propellant, and the other through hole is used for measuring the pressure of the double pulse true propellant cavity; the one-pulse ignition top cover is installed on the double pulse ignition device, a pressure measuring hole is formed in the one-pulse ignition top cover, and the pressure measuring hole is communicated with the cavity formed in the columnar hollow structure of the double pulse true propellant and bonded with the barrier.

[0014] Preferably, the material of the test container is 30CrMnSiA steel.

[0015] Preferably, the test device 1:1 simulates the composite material shell, the two-pulse charge, the grain and the partition in the engine.

[0016] The test method for the opening time of the partition of the two-pulse solid engine includes the following steps:

[0017] (1) According to the opening time s of the partition and the burning rate r of the two-pulse real grain, the thickness L of the two-pulse real grain is determined; according to the inner diameter of the combustion chamber and the thickness L of the two-pulse real grain, the thickness of the two-pulse false grain is determined; after the adiabatic layer and the sponge layer are bonded according to the design, the two-pulse false grain is installed in the combustion chamber according to the calculated thickness, and then the two-pulse real grain is installed after the two-pulse false grain is solidified, and the total assembly of the test container is performed after the two-pulse real grain is solidified.

[0018] (2) The partition is bonded to the right end surface of the two-pulse false grain and the two-pulse real grain and the inner hole surface of the two-pulse real grain; the transition section is used to connect the test container and the nozzle; the two-pulse ignition device is fixed at the left end of the test container, and the one-pulse ignition top cover is installed on the two-pulse ignition device.

[0019] (3) During the partition opening test, the two-pulse ignition device works to jet high-temperature and high-pressure gas jet to ignite the two-pulse real grain until the two-pulse real grain is completely burned; the cavity pressure before and after the opening of the partition is measured through the one-pulse ignition top cover pressure measuring hole, the pressure of the two-pulse real grain cavity is measured through the through hole on the two-pulse ignition device, the actual opening time of the partition is obtained according to the change of the cavity pressure measured at the one-pulse pressure measuring hole, and whether the actual opening time of the partition meets the requirements is judged.

[0020] (4) After the test is completed, the nozzle is detached from the test device, whether the partition opens normally according to the established mode is judged according to the state of the partition after the test, and whether there are larger fragments of the partition is checked.

[0021] (5) If the opening time of the partition does not meet the requirements or the partition does not open normally according to the established mode or there are larger fragments of the partition, the partition design does not meet the requirements; if the opening time of the partition meets the requirements and the partition opens normally according to the established mode and there are no larger fragments of the partition, the partition design meets the requirements.

[0022] (6) The opening time s of the partition is replaced, and steps (1)-(5) are repeated until all the opening times of the partitions to be tested are traversed.

[0023] Preferably, in step (1), the thickness L of the two-pulse real grain is s×r.

[0024] Preferably, in step (1), the thickness of the two-pulse false grain is the inner diameter of the combustion chamber minus the thickness L of the two-pulse real grain.

[0025] Preferably, if the opening time of the interlayer design -0.2s < the actual opening time of the interlayer < the opening time of the interlayer design +0.2s, the actual opening time of the interlayer is considered to meet the requirements.

[0026] Preferably, in steps (4) and (5), the larger fragments refer to fragments with a size not less than the inner diameter of the throat of the nozzle.

[0027] The beneficial effects of the present application compared with the prior art are:

[0028] (1) The test device of the present application is entirely made of 30CrMnSiA steel, without the need for winding and processing of the composite shell, and can directly use the metal parts of the one-pulse ignition device and the two-pulse ignition device of the full-size engine, greatly reducing the development cycle and cost.

[0029] (2) The test device of the present application uses a test container + sponge layer + dummy propellant scheme to replace the composite shell and two-pulse propellant in the full-size engine, 1:1 simulating the deformation of the full-size propellant and the interlayer in the composite shell, achieving the purpose of determining the opening time of the interlayer.

[0030] (3) According to the different viewing times, the two-pulse operation from the small time to the large time, the thickness of the two-pulse dummy propellant is reduced by machining, and the two-pulse real propellant with increased thickness is refilled, the two-pulse propellant, test container, and nozzle can be repeatedly used, greatly reducing the development cycle and cost.

[0031] (4) The test device of the present application can completely and truly reproduce the working state of the two-pulse combustion chamber of the two-pulse engine, and further determine the opening time of the interlayer, which helps to improve the understanding of the opening process of the interlayer, and also helps to optimize the interlayer, thereby improving the performance of the engine. BRIEF DESCRIPTION OF DRAWINGS

[0032] Figure 1 The present application is a schematic diagram of a test device. DETAILED DESCRIPTION

[0033] The present application will be further described below in conjunction with examples.

[0034] The present application is a new type of test device and method for the opening time of the interlayer of the axial + radial interlayer type two-pulse solid rocket engine, which can completely and truly reproduce the working state of the two-pulse combustion chamber of the two-pulse engine, and further determine the opening time of the interlayer, which helps to improve the understanding of the opening process of the interlayer, and also helps to optimize the interlayer, thereby improving the performance of the engine.

[0035] As Figure 1As shown, the device of the present application comprises a test container 3, a two-pulse false propellant 6, a two-pulse true propellant 7, an adiabatic layer 4, a sponge layer 5, a one-pulse ignition top cover 1, a two-pulse ignition device 2, a partition layer 8, a transition section 9, a nozzle 10, a sealing ring, bolts and gaskets, etc. The inner wall of the test container 3 is sequentially bonded with the adiabatic layer 4 and the sponge layer 5, which are used to simulate the deformation of the composite shell under the action of internal pressure. The sponge layer 5 is provided with the two-pulse false propellant 6, which is used to simulate the support of the two-pulse propellant column of the full-size engine on the partition layer and to control the thickness of the two-pulse true propellant 7. The cavity of the two-pulse false propellant 6 is provided with the two-pulse true propellant 7, which provides energy for viewing the opening of the partition layer at different times. The right side end surface of the two-pulse false propellant 6 and the two-pulse true propellant 7 and the inner hole surface of the two-pulse true propellant 7 are bonded with the partition layer 8; one end of the transition section 9 is fixed on the test container 3 by bolts and the partition layer is pressed tightly, and the other end of the transition section 9 is fixedly connected with the nozzle 10. The two-pulse ignition device 2 is fixed at the left end of the test container 3, and the two-pulse ignition device 2 is provided with two through holes, one of which is communicated with the two-pulse true propellant 7 for igniting the two-pulse true propellant 7, and the other is used for measuring the pressure in the two-pulse true propellant cavity; the one-pulse ignition top cover 1 is installed on the two-pulse ignition device 2, and the one-pulse ignition top cover 1 is provided with a pressure measuring hole, which is communicated with the cavity formed in the columnar hollow structure of the two-pulse true propellant 7 by bonding with the partition layer 8.

[0036] The material of the test container 3 is 30CrMnSiA steel. The test device 1:1 simulates the composite shell, two-pulse charge, propellant column and partition layer in the engine.

[0037] The method for testing the opening time of the partition layer of the double-pulse solid rocket engine comprises the following steps:

[0038] (1) According to the time s of viewing the opening of the partition layer and the burning rate r of the two-pulse true propellant, the thickness L of the two-pulse true propellant is determined; according to the inner diameter of the combustion chamber and the thickness L of the two-pulse true propellant, the thickness of the two-pulse false propellant is determined; after the adiabatic layer and the sponge layer are bonded according to the design conditions, the two-pulse false propellant is installed in the combustion chamber according to the calculated thickness value, and then the two-pulse true propellant is installed after the two-pulse false propellant is solidified, and the total assembly of the test container is carried out after the two-pulse true propellant is solidified.

[0039] The thickness L of the two-pulse true propellant is s x r. The thickness of the two-pulse false propellant is the inner diameter of the combustion chamber minus the thickness L of the two-pulse true propellant.

[0040] (2) The partition layer is bonded in the right side end surface of the two-pulse false propellant and the two-pulse true propellant and the inner hole surface of the two-pulse true propellant; the transition section is used to connect the test container and the nozzle; the two-pulse ignition device is fixed at the left end of the test container, and the one-pulse ignition top cover is installed on the two-pulse ignition device.

[0041] (3) During the diaphragm opening test, the two-pulse ignition device works, high-temperature and high-pressure gas jet is ejected, the two-pulse true charge is ignited until the two-pulse true charge is completely burned out; the cavity pressure before and after the diaphragm opening after the two-pulse true charge is ignited is measured through the diaphragm opening test pressure hole of the one-pulse ignition top cover, the pressure of the two-pulse true charge cavity is measured through the through hole of the two-pulse ignition device, the actual opening time of the diaphragm is obtained according to the cavity pressure change measured at the one-pulse pressure hole, and whether the actual opening time of the diaphragm meets the requirements is judged.

[0042] If the actual opening time of the diaphragm is -0.2s < the actual opening time of the diaphragm < the designed opening time of the diaphragm + 0.2s, it is considered that the actual opening time of the diaphragm meets the requirements.

[0043] (4) After the test is completed, the nozzle is detached from the test device, whether the diaphragm normally opens in the established way is judged according to the state of the diaphragm after the test, and whether the diaphragm has larger fragments is checked.

[0044] The larger fragments refer to fragments with a size not less than the inner diameter of the throat of the nozzle.

[0045] (5) If the opening time of the diaphragm does not meet the requirements or the diaphragm does not normally open in the established way or the diaphragm has larger fragments, the diaphragm design does not meet the requirements; if the opening time of the diaphragm meets the requirements and the diaphragm normally opens in the established way and the diaphragm has no larger fragments, the diaphragm design meets the requirements.

[0046] (6) The opening time s of the diaphragm is replaced, steps (1)-(5) are repeated until all the opening times of the diaphragm to be tested are traversed.

[0047] Although the present application has been disclosed with the above preferred embodiments, it is not intended to limit the present application, and any person skilled in the art can make possible changes and modifications to the technical solutions of the present application by using the disclosed methods and technical contents without departing from the spirit and scope of the present application, therefore, any simple modification, equivalent change and modification made to the above embodiments according to the technical essence of the present application, which does not depart from the content of the technical solutions of the present application, all belong to the protection scope of the technical solutions of the present application.

Claims

1. A device for testing the state of a double-pulse solid-propellant engine diaphragm opening at different times, characterized in that it comprises: It comprises a test container (3), a two-pulse false propellant (6), a two-pulse true propellant (7), an adiabatic layer (4), a sponge layer (5), a one-pulse ignition top cover (1), a two-pulse ignition device (2), a partition layer (8), a transition section (9), and a nozzle (10). The inner wall of the test container (3) is sequentially bonded with the adiabatic layer (4) and the sponge layer (5), the sponge layer (5) is placed with the two-pulse false propellant (6), the two-pulse true propellant (7) is placed in the columnar hollow structure of the two-pulse false propellant (6), and the right side end surface of the two-pulse false propellant (6) and the two-pulse true propellant (7) and the inner hole surface of the two-pulse true propellant (7) are bonded with the partition layer (8); one end of the transition section (9) is fixed on the test container (3) through bolts, the transition section (9) and the test container (3) press the partition layer, and the other end of the transition section (9) is fixedly connected with the nozzle (10); The two-pulse ignition device (2) is installed on the left end of the test container (3) through bolts, the two-pulse ignition device (2) is provided with two through holes, one of which is communicated with the two-pulse true propellant (7) for igniting the two-pulse true propellant (7), and the other is used for measuring the pressure of the two-pulse true propellant cavity; the one-pulse ignition top cover (1) is installed on the two-pulse ignition device (2), and the one-pulse ignition top cover (1) is provided with a pressure measuring hole communicated with the cavity formed in the columnar hollow structure of the two-pulse true propellant (7) by bonding with the partition layer (8); The sponge layer is used for simulating the deformation of the composite material shell under the action of internal pressure; the two-pulse false propellant is used for simulating the supporting effect of the full-size engine two-pulse propellant column on the partition layer and controlling the thickness of the two-pulse true propellant.

2. The dual pulse solid motor barrier open time state test device of claim 1, wherein: The test container (3) is made of 30CrMnSiA steel.

3. The dual pulse solid motor barrier open time state test device of claim 1, wherein: The test device 1:1 simulates the composite material shell, two-pulse charge, propellant column and partition layer in the engine.

4. A method for testing the state of the double-pulse solid-propellant engine partition opening at different times, according to the double-pulse solid-propellant engine partition opening state testing device of any one of claims 1-3, characterized in that, It comprises the following steps: (1) According to the opening time s of the partition layer and the burning rate r of the two-pulse true propellant, the thickness L of the two-pulse true propellant is determined; according to the inner diameter of the combustion chamber and the thickness L of the two-pulse true propellant, the thickness of the two-pulse false propellant is determined; after the adiabatic layer and the sponge layer are bonded according to the design condition, the two-pulse false propellant is installed in the combustion chamber according to the calculated thickness value, the two-pulse true propellant is installed after the two-pulse false propellant is solidified, and the test container is assembled after the two-pulse true propellant is solidified; the thickness L of the two-pulse true propellant is s x r, and the thickness of the two-pulse false propellant is the inner diameter of the combustion chamber minus the thickness L of the two-pulse true propellant; (2) The partition layer is bonded on the right side end surface of the two-pulse false propellant and the two-pulse true propellant and the inner hole surface of the two-pulse true propellant; the transition section is used to connect the test container and the nozzle; the two-pulse ignition device is fixed on the left end of the test container, and the one-pulse ignition top cover is installed on the two-pulse ignition device; (3) During the partition layer opening test, the two-pulse ignition device works, high-temperature and high-pressure gas jet is ejected, the two-pulse true propellant is ignited, and the two-pulse true propellant is completely burned until the two-pulse true propellant is completely burned. The pressure in the cavity before and after the opening of the partition is measured by a pulse ignition top cover pressure measuring hole after the second pulse true propellant is ignited, the pressure in the second pulse true propellant cavity is measured through a through hole on the second pulse ignition device, the actual opening time of the partition is obtained according to the pressure change in the cavity measured by the first pulse pressure measuring hole, and whether the actual opening time of the partition meets the requirements is judged; (4) After the test is completed, the nozzle is detached from the test device, whether the partition opens normally in the established manner is judged according to the state of the partition after the test, and whether the partition has large fragments is checked; (5) If the opening time of the partition does not meet the requirements or the partition does not open normally in the established manner or the partition has large fragments, the partition design does not meet the requirements; returning to if the opening time of the partition meets the requirements and the partition opens normally in the established manner and the partition has no large fragments, the partition design meets the requirements; (6) The opening time s of the partition is replaced, and steps (1)-(5) are repeated until all opening times of the partitions to be tested are traversed.

5. The dual pulse solid motor barrier open time state test method of claim 4, wherein, If the actual opening time of the partition is-0.2s 6. The dual pulse solid motor barrier open time state test method of claim 4, wherein, In steps (4) and (5), the large fragments refer to fragments with a size not less than the inner diameter of the throat of the nozzle.

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