A ground test system and method for simulating high-g separation of a rocket

Abstract

The application provides a repeated simulation ground test system and method for high overload separation of a rocket, comprising a separation overload simulation table, a power assembly and a pipeline system, the separation overload simulation table provides a movement track, a movement part of the power assembly moves linearly along the movement track under the action of power, and the pipeline of the pipeline system provides power through power quality delivered in the pipeline. The application provides a repeated high overload ground separation test system and design method, and an implementation method of the test system, and can be used for simulating fairing separation test of a carrier rocket. The application belongs to the technical field of carrier rockets, and when the separation time sequence of the rocket is set to start fairing separation in a flight active stage, 1.5g-3.5g overload exists in the axial direction. The application realizes the overload size and overload time of the overload environment of the simulated separation through overload design, realizes the target overload through the overload test table, the cylinder assembly and the pipeline system and other parts, and achieves the effect of simulating the fairing separation environment.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of ground test of launch vehicle, and particularly relates to a ground test system and method for repeatedly simulating high-overload separation of launch vehicle. BACKGROUND

[0002] The launch vehicle usually sequentially performs multi-stage separation in the flight process, such as first-stage separation, second-stage separation, third-stage separation and fairing separation, and axial overload is generated in each stage separation process. The separation of the fairing of the launch vehicle is a complex and precise process, and any error will lead to separation failure. In order to reduce the risk of separation failure of the fairing of the launch vehicle, verify the rationality of the fairing separation design, and the feasibility and reliability of the fairing separation process, the fairing separation process needs to be simulated in the ground environment. In order to improve the carrying efficiency of the launch vehicle, the separation timing is set to start the fairing separation at the flight main active stage, at which time the launch vehicle has a high overload of 1.5g-3.5g in the axial direction. In order to repeatedly simulate the high-overload environment of the fairing separation in the actual flight process, a ground test system for repeatedly simulating high-overload separation of launch vehicle needs to be designed. SUMMARY

[0003] The present application provides a ground test system and method for repeatedly simulating high-overload separation of launch vehicle, which can repeatedly simulate the high-overload environment of the launch vehicle separation in the main active stage.

[0004] The technical scheme of the present application is as follows:

[0005] A ground test system for repeatedly simulating high-overload separation of launch vehicle, comprising a separation overload simulation table, a power assembly and a pipeline system, the separation overload simulation table provides a motion track, the motion part of the power assembly moves linearly along the motion track under the action of power (to simulate the separation overload), and the pipeline of the pipeline system provides power for the motion part by conveying working substance in the pipeline.

[0006] Further, the pipeline system is a gas pipeline system, which comprises a gas cylinder, a manual valve, a gas charging valve, a second electromagnetic valve and N cylinder assemblies in sequence along the pipeline, N being a natural number.

[0007] The cylinder assembly sequentially comprises a cylinder rod end, a cylinder rod, a cylinder barrel sleeved outside the cylinder rod, a piston located in the cylinder barrel and in contact with the tail of the cylinder rod, and a throttle hole (which allows the gas to push the piston to move) communicating with the inner cavity of the cylinder barrel, and the cylinder rod end abuts against the motion part in the initial state (to push the motion part to move linearly along the motion track).

[0008] Further, the gas pipeline system further comprises a first electromagnetic valve, which is arranged on the pipeline between the second electromagnetic valve and the cylinder assembly.

[0009] Further, the gas pipeline system further comprises an adapter of M passages, M≥3, being a natural number; accordingly, the number of the cylinder assemblies N=M-1.

[0010] Preferably, N is even, which is beneficial to the balance of the stress points.

[0011] The application also provides a ground test method for repeatedly simulating high-overload separation of a rocket, based on the aforementioned ground test system for repeatedly simulating high-overload separation of a rocket, comprising the following steps:

[0012] The target simulation overload is n g, and the cylinder overload a(t) is calculated according to the initial pressure of the gas cylinder, the volume of the cylinder, the volume of the pipeline, and the throttle aperture of the cylinder. The required overload a(t) is achieved through multiple rounds of iterative calculation by changing the initial volume of the gas cylinder, the pressure of the gas cylinder, and the throttle aperture and radius R2 of the cylinder.

[0013] Further, the calculation of the cylinder overload a(t) according to the initial pressure of the gas cylinder, the volume of the cylinder, the volume of the pipeline, and the throttle aperture of the cylinder specifically comprises

[0014] The gas mass m0 in the gas cylinder is calculated according to the gas state equation:

[0015] m0=P0V0 / R0 / T0

[0016] wherein P0(MPa) is the initial pressure of the gas cylinder after the pressure reducing valve; V0(m3) is the volume of the gas cylinder; R0=287 J / (K·kg) is the gas constant; and T0(K) is the initial temperature of the gas cylinder. 3

[0017] The gas mass m1 in the pipeline is calculated according to the following equation:

[0018] m1=ρv1

[0019] wherein ρ is the gas density, v1 is the initial volume of the pipeline, and R1(m) is the inlet radius of the pipeline.

[0020] The gas mass m2 in the cylinder is calculated according to the following equation:

[0021] m2=ρv2

[0022] wherein ρ is the gas density, and v2 is the initial volume of the cylinder.

[0023] The opening time t of the electromagnetic valve is 0-tts, and tts is 0.005-0.2 s (0.03 s in this example). The process of opening the electromagnetic valve for 0-tts s is approximately regarded as linearly increasing the radius of the pipeline from 0 to bm, so that when t≤tt, R1=bt / tt.

[0024] When t>tt, R1=b.

[0025] The gas mass m in the pipeline is calculated according to the following empirical formula of gas flow:​i (t+dt) :

[0026] m1(t+dt) = m1(t) - dm2(t) + 5470.8P0R1 2 u1(t) / T0 / 1000000 · dt

[0027] where dm2(t) is the mass of gas flowing out of the pipe, u1(t) is the velocity of gas flowing into the pipe, and T0 is the temperature

[0028] According to the aerodynamic formula, the static pressure P1(t) in the pipe is:

[0029] P1(t) = R0T0m1(t) / v1

[0030] According to the aerodynamic formula, the total pressure P2(t) in the pipe is:

[0031] P2(t) = P1(t) + 0.25u1(t) 2 (m1(t) - m1) / v1

[0032] The pressure P0(t) in the cylinder changes with time:

[0033] P0(t) = (1 - (m1(t) + m2(t)) / m0)P0

[0034] where m2(t) is the mass of gas in the cylinder, and P0 is the initial pressure of the cylinder;

[0035] When P2(t) / P0 > 0.528, u1(t) = c · (5 · ((P1(t) / P0(t))^0.2857143 - 1)) 1 / 2

[0036] When P2(t) / P0 ≤ 0.528, u1(t) = c, and c is the speed of sound;

[0037] According to the empirical formula of gas flow, the mass of gas m2(t+dt) in the cylinder is calculated:

[0038] m2(t+dt) = m2(t) + 5470.8P1(t) · R2^2 · u2(t) / T0 / 1000000dt

[0039] According to the aerodynamic formula, the static pressure P3(t) in the cylinder is:

[0040] P3(t) = R0Tm2(t) / v2

[0041] According to the aerodynamic formula, the total pressure P4(t) in the cylinder is:

[0042] P4(t) = P3(t) + 0.25u2(t)∧2(m2(t)-m2) / v2

[0043] When P4(t) / P2(t)>0.528, u2(t)=c·(5·((P3(t) / P1(t))^0.2857143-1)) 1 / 2 , u2(t) is the flow velocity of the gas flowing into the cylinder;

[0044] When P2(t) / P0≤0.528, u1(t)=c, c is the speed of sound;

[0045] The acceleration a(t) of the overload platform:

[0046] a(t)=0.9N(P4(t)-P w )A0 / M

[0047] Where A0 is the piston area of the cylinder, A0=πR0 2 , the mass of the overload platform M (kg) ; Pw is the friction of the cylinder;

[0048] The velocity increment v(t+dt):

[0049] v(t+dt)=v(t)+a(t)dt

[0050] The motion stroke S(t) of the cylinder:

[0051] S(t+dt)=v(t+dt)dt+0.5a(t+dt)dt^2+S(t)

[0052] When the motion stroke S(t) of the cylinder is greater than or equal to L (in Table 1), the cylinder stroke ends, and the overload platform stops moving;

[0053] Where R2 (m) is the radius of the cylinder throttle hole; R3 (m) is the radius of the cylinder; S(t) is the motion stroke of the cylinder L (m) ; V1 is the initial volume of the cylinder m 3 .

[0054] In another aspect, the application also provides a computer-readable storage medium, which comprises a stored program, wherein the program performs the above-mentioned repeated simulation of the ground test method for high-overload separation of a rocket.

[0055] In another aspect, the application also provides an electronic device comprising a memory and a processor, wherein the memory stores a computer program, and the processor is configured to execute the aforementioned repeated simulation of the ground test method for high-overload separation of a rocket by using the computer program.

[0056] The above technical solutions conceived by the application can achieve the following beneficial effects compared with the prior art:

[0057] The application provides a high-overload repeatable ground separation test system and a design method, and an implementation method of the test system, which can be used for simulating fairing separation test of a carrier rocket. The application belongs to the technical field of carrier rockets, and when the separation time sequence of the rocket is set to start the fairing separation in the main active phase of flight, there is an axial overload of 1.5g-3.5g at this time. The application realizes the overload size and overload time of the simulated separation overload environment through overload design, realizes the target overload through the overload test bench, the cylinder assembly and the pipeline system and other components, and achieves the effect of simulating the fairing separation environment. The overload size and the overload providing time are adjusted by adjusting the pressure of the gas cylinder, the cavity, the cylinder throttling aperture, the opening process of the pilot type electromagnetic valve is considered, and an overload calculation method is proposed. The overload is calculated before the test, and after multiple rounds of iterative calculation, the target overload requirement is met.

[0058] The overload size is designed by the following method. The cylinder overload size is calculated by considering the initial pressure of the gas cylinder, the cavity, the pipeline cavity and the cylinder throttling aperture. By changing the initial cavity, pressure and throttling aperture of the gas cylinder, the required overload a(t) requirement can be realized through multiple rounds of iterative calculation.

[0059] The application provides an overload adjusting device, which realizes the adjustment of the overload size and the overload providing time of the overload system by adjusting the pressure size of the gas cylinder and the cylinder throttling aperture. The separation device is a separation cylinder, and the structure is a "cylinder body + push rod" structure, which has a guiding effect. The end of the cylinder rod is provided with external threads, and the end of the cylinder rod is provided with internal threads. The end of the cylinder rod is installed at one end of the cylinder rod, and the length of the "cylinder rod + cylinder rod end" can be adjusted by rotating the end of the cylinder rod. After the cylinder assembly is installed in place, the length of the "cylinder rod + cylinder rod end" can be adjusted by rotating the end of the cylinder rod. On the one hand, the length is adjusted to ensure that the end of the cylinder rod is on the disc support, and on the other hand, the cylinder stroke can also be adjusted. The end of the cylinder rod and the disc support of the overload test bench are fixed by a clamping plate, so that the cylinder rod will not be thrown away, reducing the risk of injury caused by the throwing of the cylinder rod. The test system is triggered by remotely controlling the electromagnetic valve, and the safety risk is low. BRIEF DESCRIPTION OF DRAWINGS

[0060] Figure 1 It is a schematic diagram of the whole overload test bench.

[0061] Figure 2 It is a schematic diagram of the pipeline system.

[0062] Figure 3 It is a schematic diagram of the cylinder assembly.

[0063] Figure 4 It is a flow chart of the design of the overload system.

[0064] Figure 5The overload curve of the overload design example is designed, the horizontal coordinate represents the opening time process of the electromagnetic valve, the vertical coordinate represents the process within 0.3s of the opening time of the electromagnetic valve, and 0.3s is matched with the cylinder stroke.

[0065] Reference signs:

[0066] 1-overload test bench; 2-first cylinder assembly; 3-pipeline; 4-first electromagnetic valve; 5-adaptor of M passages (four passages in the example); 6-second electromagnetic valve; 7-hand valve; 8-gas cylinder; 9-gas filling valve; 10-second cylinder assembly; 101-plate; 11-cylinder rod end; 12-cylinder rod; 13-front retainer ring; 14-cylinder barrel; 15-piston; 16-rear retainer ring; 17-throttle hole; 1a-base; 2a-stand; 3a-disc support; 4a-linear guide rail; 5a-driving mechanism; 7a-support back block, 8a-suspension ring, 9a-limiting plate, 10a-sliding block, 11a-supporting piece. DETAILED DESCRIPTION

[0067] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the protection scope of the present application.

[0068] The present invention provides a ground test system for repeatedly simulating the high-overload separation of a rocket, which includes a separation overload simulation platform, a power component, and a pipeline system. The separation overload simulation platform provides a motion track, and the moving part of the power component moves linearly along the motion track under the action of power. The pipeline of the pipeline system provides power for the moving part through the working medium conveyed in the pipeline. The pipeline system is a gas pipeline system, which includes a gas cylinder. Starting from the gas cylinder, the pipeline includes a manual valve, an inflation valve, a second solenoid valve, and N cylinder assemblies in sequence, where N is a natural number 2. The cylinder assembly sequentially includes a cylinder rod end, a cylinder rod, a cylinder barrel sleeved outside the cylinder rod, a piston located inside the cylinder barrel and contacting the tail of the cylinder rod, and a throttle hole communicating with the inner cavity of the cylinder barrel (introducing gas to push the piston to move). The cylinder rod end abuts against the moving part in the initial state (pushing the moving part to move linearly along the motion track). The piston and the cylinder rod are in contact. The piston pushes the cylinder rod to move. After the stroke is completed, the piston is blocked by the front retaining ring of the cylinder, and the cylinder rod is separated from the cylinder barrel along with the disc support. The gas pipeline system further includes a first solenoid valve, and the first solenoid valve is arranged on the pipeline between the second solenoid valve and the cylinder assembly. The gas pipeline system further includes an adapter with M passages, where M≥3. In this embodiment, M is a natural number 4, a four-way joint, and also includes a three-way joint, which is determined according to the needs of the system pipeline. The separation overload simulation platform includes a base, a column, a disc support, two linear guides, and a driving mechanism. Among them, the base, the column, and the disc support are all provided with lifting holes or lifting rings for lifting each component. In this embodiment, they are all set as lifting rings, and the lifting rings are installed on each component through bolts and nuts. The column is vertically installed in the center of the base welded by an "L"-shaped steel beam. It is fixedly connected by screws. A limiting plate is provided at the top of the column for limiting the upward movement of the disc support to the maximum displacement. An elastic member is adhered to the surface of one side of the limiting plate connected to the column for buffering the impact on the limiting plate when the disc support moves upward. A plurality of linear guides are vertically fixedly installed on the column along the length direction of the column. In this embodiment, there are two linear guides, which are respectively arranged in parallel on the two edges on one side of the column. The bottom surface of the guide rail of the linear guide is fitted and installed with the column by screws or welding to provide a track for the up and down movement of the disc support. It further includes a support member, which can be a flat plate or a ring structure for supporting the disc support. In this embodiment, the support member is a support flat plate. The center of the support flat plate passes through the column and is fixedly installed on the column by screws. The support flat plate is parallel to the horizontal plane. The middle part of the disc support is a hollow structure and is placed on the support flat plate through the column. A slider matched with the linear guide is arranged in the linear guide. In this embodiment, each linear guide corresponds to a slider, and each slider is connected to the disc support through a support back block and can slide along the length direction of the linear guide. The support back block is a trapezoidal structure. The bottom of the support back block is connected to the disc support by screws, and the side is connected to the slider of the linear guide by screws.In this embodiment, the driving mechanism consists of several cylinders, preferably two cylinders symmetrically arranged below the disc support, vertically mounted on the base. The two cylinders are connected to an external air source via pipelines. After air is supplied through the pipelines, the cylinder rods move upwards, thereby pushing the disc support upwards. Simultaneously, to measure the acceleration of the disc support during testing, an accelerometer sensor can be installed on the disc support to sense overload, i.e., acceleration. This sensor has a sampling frequency of no less than 800Hz, uses wired transmission, and is specifically a nine-axis high-precision attitude angular velocity sensor. A laser sensor can also be used, but the cost is higher.

[0069] This embodiment also provides a ground test method for repeatedly simulating high-overload separation of a rocket. Based on the ground test system for repeatedly simulating high-overload separation of a rocket, it can be used to simulate the overload environment of 1.5g to 3.5g during the separation of the active phase of a launch vehicle, and includes the following steps:

[0070] The target simulated overload is determined to be 3g. The cylinder overload size is calculated based on the initial pressure of the gas cylinder, the cylinder cavity, the pipeline cavity, and the cylinder throttling orifice diameter. By changing the initial cylinder cavity, the gas cylinder pressure, the cylinder throttling orifice diameter, and the cylinder throttling orifice radius R2, the required overload a(t) is achieved through multiple rounds of iterative calculations.

[0071] like Figure 1 As shown, the cylinder assembly is installed on the overload test bench, and the cylinder is fixed to the base of the overload test bench by the cylinder rear end cover. The length of the cylinder rod and cylinder rod end is adjusted so that the cylinder rod end rests on the disc support of the overload test bench, and then the cylinder rod end is fixed to the disc support of the overload test bench by a clamping plate. The manual valve of the gas cylinder is opened, and the gas cylinder is filled to the target pressure through the filling valve connection. After filling is complete, the filling valve of the gas cylinder is closed. The second solenoid valve is opened, and airflow enters the cylinder through the pipeline. The cylinder pushes the disc support to move. After the cylinder rod reaches its stroke limit, the piston is limited by the cylinder front retaining ring, and the cylinder rod is pulled out of the cylinder barrel. After the cylinder stroke reaches its limit, the first solenoid valve is opened to release the airflow in the pipeline.

[0072] This invention provides a ground test system for simulating high-overload separation of a rocket, comprising an overload test platform, cylinder assemblies, a piping system, and gas cylinders. Based on this system, a ground test method for simulating high-overload separation of a rocket is designed, specifically including a piping pressure control method and a pressure calculation method. The piping system includes a manual valve, a charging valve, a second solenoid valve, a first solenoid valve, pipes, four-way valves, and three-way valves. The gas piping system also includes M adapters with M ≥ 3, where M is a natural number. Correspondingly, the number of cylinder assemblies is N = M-1. In this example, N is 2, with two cylinder assemblies, which facilitates force balance.

[0073] Each cylinder assembly contains a push rod, a cylinder rod end, a clamping plate, a front retaining ring, a cylinder barrel, a piston, a rear retaining ring, and a throttle hole, which is specifically arranged on the rear end cover of the cylinder and is used for adjusting the flow rate of the gas flow.

[0074] The rear end cover of the cylinder has a throttle hole for adjusting the flow rate of the gas flow.

[0075] The above-mentioned gas circuit system is designed, and the entire movement process is divided into three stages: a pressure building stage, a pressure stabilizing stage, and a pressure reducing stage. Assuming that the entire process is a constant temperature process, the temperature T0 is 293 K, and after multiple rounds of iterative calculations, the 3g overload requirement can be achieved, and the design parameters are shown in Table 1. The ground test method for repeatedly simulating high overload separation of a rocket is simulated, and based on the aforementioned ground test system for repeatedly simulating high overload separation of a rocket, the 3g overload system design parameters are shown in Table 1, including the following steps:

[0076] Table 1 3g Overload System Design Parameters

[0077]

[0078]

[0079] The target simulated overload is determined to be 3g, the cylinder overload size is calculated according to the initial pressure of the gas cylinder, the cavity, the pipeline cavity and the cylinder throttle hole diameter, the initial cavity of the gas cylinder, the pressure of the gas cylinder and the cylinder throttle hole diameter are changed, the cylinder throttle hole radius R2 is changed, and after multiple rounds of iterative calculations, the required overload a(t) requirement is achieved.

[0080] The gas mass m0 in the gas cylinder is calculated according to the gas state equation:

[0081] m0 = P0V0 / R0 / T0

[0082] Wherein P0 = 4 × 10 6 Pa, V0 = 6.8 × 10 -3 m 3 , R0 = 287 J / (K·kg).

[0083] Wherein the gas mass m1 in the pipeline is calculated:

[0084] m1 = ρv1

[0085] Wherein ρ is the gas density, v1 is the initial cavity of the pipeline, and R1(m) is the inlet radius of the pipeline;

[0086] Wherein the gas mass m2 in the cylinder is calculated:

[0087] m2 = ρv2

[0088] Wherein ρ is the gas density, and v2 is the initial cavity of the cylinder, i.e., the volume;

[0089] The electromagnetic valve opening time t is 0-tt, tt is 0.005-0.2s (tt is 0.03s in the example) ; the process of electromagnetic valve opening 0-tt s is approximately regarded as that the pipeline radius linearly increases from 0 to b (m), b is 0.006m in the example, the value cannot be too thin or too thick, therefore

[0090] When t≤tt, R1=bt / tt; when t≤0.03, R1=6×10 -3 t / 0.03;

[0091] When t>tt, R1=b; when t>0.03, R1= 6 × 1 0 -3 ;

[0092] In the pipeline, the gas mass m1 (t+dt) in the pipeline is calculated according to the gas flow empirical formula:

[0093] m1 (t+dt)=m1 (t)-dm2 (t)+5470.8P0R1 2 u1 (t) / T0 / 1000000·dt

[0094] In the formula, m1 (t) is the gas mass in the pipeline, dm2 (t) is the gas mass flowing out of the pipeline, u1 (t) is the gas flow velocity flowing into the pipeline, and T0 is the temperature;

[0095] According to the air dynamics formula, the static pressure P1 (t) in the pipeline is:

[0096] P1 (t)=R0T0m1 (t) / v1

[0097] According to the air dynamics formula, the total pressure P2 (t) in the pipeline is:

[0098] P2 (t)=P1 (t)+0.25u1 (t) 2 (m1 (t)-m1) / v1

[0099] The pressure P0 (t) in the cylinder changes with time:

[0100] P0 (t)=(1-(m1 (t)+m2 (t)) / m0)P0

[0101] In the formula, m2 (t) is the gas mass in the cylinder, and P0 is the initial pressure of the cylinder;

[0102] When P2 (t) / P0>0.528, u1 (t)=c·(5·((P1 (t) / P0 (t))^0.2857143-1)) 1 / 2 ,

[0103] When P2(t) / P0≤0.528, u1(t)=c, c is the speed of sound;

[0104] The gas mass m2(t+dt) in the cylinder is calculated according to the gas flow empirical formula:

[0105] m2(t+dt)=m2(t)+5470.8P1(t)·R2^2·u2(t) / T0 / 1000000dt

[0106] The static pressure P3(t) in the cylinder is calculated according to the aerodynamic formula:

[0107] P3(t)=R0Tm2(t) / v2;

[0108] The total pressure P4(t) in the cylinder is calculated according to the aerodynamic formula:

[0109] P4(t)=P3(t)+0.25u2(t)^2(m2(t)-m2) / v2;

[0110] When P4(t) / P2(t)>0.528, u2(t)=c·(5·((P3(t) / P1(t))^0.2857143-1)) 1 / 2 , u2(t) is the gas flow velocity flowing into the cylinder;

[0111] When P2(t) / P0≤0.528, u1(t)=c, c is the speed of sound;

[0112] The acceleration a(t) of the overload platform.

[0113] a(t)=0.9N(P4(t)-P w )A0 / M

[0114] Where A0 is the piston area of the cylinder, A0=πR0 2 , the mass M(kg) of the overload platform; P W is the cylinder friction, P W Generally, 0.1 MPa; first, only the gas mass in one cylinder is calculated, then the total pressure of one cylinder is derived, and finally when calculating the acceleration, the number N of cylinders is multiplied;

[0115] The velocity increment v(t+dt):

[0116] v(t+dt)=v(t)+a(t)dt

[0117] The cylinder motion stroke S(t):

[0118] S(t+dt)=v(t+dt)dt+0.5a(t+dt)dt^2+S(t)

[0119] When the cylinder motion stroke S(t) >= L (in Table 1), the cylinder stroke ends, and the overload platform stops moving;

[0120] Wherein, the cylinder throttle hole radius R2 (m); the cylinder radius R3 (m); the cylinder stroke S(t) = L (m); the cylinder initial volume V1 m 3 Wherein, the overload size is designed by the following method, considering the initial pressure of the gas cylinder, the volume, the pipeline volume, and the cylinder throttle hole diameter to calculate the cylinder overload size, by changing the initial pressure of the gas cylinder, the volume, and the throttle hole diameter, through multiple rounds of iterative calculation, the required overload a(t) can be achieved. In this example, the cylinder motion stroke S(t) is 0.3s, Figure 5 is a process curve of 0~0.3s, which matches the cylinder motion stroke S(t), and it can be seen from the figure that the overload of not less than 2.0g is not less than 0.1s. Adding the gravity overload 1.0g, the overload can reach 3g during the whole process. After the stroke ends, the overload is 1g.

[0121] It can also be considered that the present application provides an overload adjusting device, which adjusts the overload size and the overload providing time length of the overload system by adjusting the gas cylinder pressure size and the cylinder throttle hole diameter.

[0122] The overload power driving mechanism is a cylinder assembly, which has a guiding effect in the structure form of "cylinder body + push rod".

[0123] The cylinder rod is provided with a cylinder rod end head with adjustable length, and the length of "cylinder rod + cylinder rod end head" can be adjusted within a certain range. After the cylinder assembly is installed in place, the cylinder rod end head can be fixed on the disc support of the overload test platform through the clamping plate by screwing the cylinder rod end head, so that the cylinder rod will not be thrown away, reducing the risk of injury caused by throwing away the cylinder rod.

[0124] The test system is triggered by remotely controlling the electromagnetic valve, and the safety risk is low.

[0125] The cylinder assembly is installed on the overload test platform, the cylinder rod is adjusted to be clamped on the disc support of the overload test platform by the cylinder rod end head, and the cylinder rod end head is fixed on the disc support of the overload test platform by the clamping plate. Open the hand valve of the gas cylinder, inflate the gas cylinder to the target pressure through the inflation valve connection, close the inflation valve of the gas cylinder after inflation is completed; open the second electromagnetic valve, and the gas flow enters the cylinder through the pipeline; the cylinder pushes the overload platform to move; after the cylinder rod stroke is in place, the piston is limited by the cylinder front stop ring, and the cylinder rod is pulled out of the cylinder barrel; after the cylinder stroke is in place, the first electromagnetic valve is opened to release the gas flow in the pipeline.

[0126] Compared with the prior art, the present application has the following beneficial effects:

[0127] The application considers initial pressure of gas cylinder, cavity, pipeline cavity, cylinder throttle aperture and the like to calculate size of cylinder overload, and provides a design calculation method of a repeatable high-overload ground test system, which can realize adjustment of required overload size and overload providing time, can provide a high-overload environment for fairing separation ground test, and further provides a pipeline system for adjusting pressure and a cylinder assembly for providing thrust, and the test system triggering is remotely controlled through an electromagnetic valve, and safety risk is low.

[0128] The application provides a computer readable storage medium, which comprises a stored program, wherein the program performs the above-mentioned repeated ground test method for simulating high-overload separation of a rocket.

[0129] The application further provides an electronic device, which comprises a memory and a processor, the memory stores a computer program, and the processor is configured to execute the computer program to perform the repeated ground test method for simulating high-overload separation of a rocket.

Claims

1. A ground test system for simulating repeated high-g rocket separation, comprising The system comprises a separate overload simulation platform, a power assembly and a pipeline system, the overload simulation platform provides a movement track, the movement part of the power assembly moves linearly along the movement track under the action of power, and the pipeline of the pipeline system provides power for the movement part by the power quality conveyed in the pipeline; The pipeline system is a gas pipeline system, comprising a gas cylinder, a manual valve, a gas charging valve, a second electromagnetic valve and N cylinder assemblies in sequence along the pipeline, wherein N is a natural number. The cylinder assembly comprises a cylinder rod end, a cylinder rod, a cylinder barrel sleeved outside the cylinder rod, a piston in the cylinder barrel and in contact with the tail of the cylinder rod, and a throttle hole in communication with the inner cavity of the cylinder barrel, and the cylinder rod end abuts against the movement part in the initial state.

2. The ground test system for repeated simulated high g-rocket separation of claim 1, wherein The gas pipeline system further comprises a first electromagnetic valve arranged on the pipeline between the second electromagnetic valve and the cylinder assembly.

3. The ground test system for repeated simulated rocket high-G-separation of claim 1, wherein The gas pipeline system further comprises an adapter with M passages, wherein M is greater than or equal to 3 and is a natural number; accordingly, the number of cylinder assemblies N is M-1.

4. The ground test system for repeated simulated rocket high- G- level separation of claim 1, wherein Preferably, N is an even number.

5. A method of repeating ground test of simulated high overload separation of a rocket based on the ground test system of simulated high overload separation of a rocket according to any one of claims 1 to 4, characterized in that The method comprises the following steps: determining a target simulation overload of n g, calculating the size of the cylinder overload according to the initial pressure of the gas cylinder, the volume, the pipeline volume and the cylinder throttle hole diameter, changing the initial volume of the gas cylinder, the pressure of the gas cylinder and the cylinder throttle hole diameter, the cylinder throttle hole radius R2, and achieving the required overload a(t) through multiple rounds of iterative calculation; The calculation of the size of the cylinder overload a(t) according to the initial pressure of the gas cylinder, the volume, the pipeline volume and the cylinder throttle hole diameter specifically comprises calculating the gas mass m0 in the gas cylinder according to the gas state equation: m0 = P0V0 / R0 / T0 Wherein, the initial pressure of the gas cylinder P0(MPa), after the pressure reducing valve; the volume of the gas cylinder V0(m 3 ); R0=287J / (K·kg); wherein the gas mass m1 in the pipeline is calculated as: m1 = ρv1 wherein ρ is the gas density, v1 is the initial volume of the pipeline, and R1(m) is the inlet radius of the pipeline; wherein the gas mass m2 in the cylinder is calculated as: m2 = ρv2 wherein ρ is the gas density, and v2 is the initial volume of the cylinder, i.e. the volume; The opening time t of the electromagnetic valve is 0-tts, and tt is 0.005-0.2s (0.03s in this example); the process of the electromagnetic valve opening for 0-tts is approximately regarded as that the pipeline radius linearly increases from 0 to b, so that when t≤tt, R1=bt / tt; when t>tt, R1=b; The gas mass m1(t+dt) in the pipeline is calculated according to the gas flow empirical formula: m1(t+dt) = m1(t) - dm2(t) + 5470.8POR1 2 u1(t) / T0 / 1000000 · dt wherein dm2(t) is the gas mass flowing out of the pipeline, u1(t) is the gas flow velocity flowing into the pipeline, and T0 is the temperature The static pressure P1(t) in the pipeline is calculated according to the aerodynamics formula: P1(t) = R0T0m1(t) / v1 The total pressure P2(t) in the pipeline is calculated according to the aerodynamics formula: P2(t) = P1(t) + 0.25u1(t) 2 (m1(t) - m1) / v1 The pressure P0(t) in the gas cylinder changes with time: P0(t) = (1-(m1(t)+m2(t)) / m0)P0 wherein m2(t) is the gas mass in the cylinder, and P0 is the initial pressure of the gas cylinder; u1(t) = c • (5 • ((P1(t) / P0(t))0.2857143-1) when P2(t) / P0> 0.528 1 / 2 when P2(t) / P0≤0.528, u1(t)=c, and c is the sound speed; The gas mass m2(t+dt) in the cylinder is calculated according to the gas flow empirical formula: m2(t+dt)=m2(t)+5470.8P1(t)R2^2u2(t) / T0 / 1000000dt According to the aerodynamic formula, the static pressure P3(t) in the cylinder is: P3(t)=R0Tm2(t) / v2 According to the aerodynamic formula, the total pressure P4(t) in the cylinder is: P4(t)=P3(t)+0.25u2(t)^2(m2(t)-m2) / v2 u2(t) = c · (5 · ((P3(t) / P1(t))0.2857143-1) when P4(t) / P2(t) > 0.528 1 / 2 u2(t) = c · (5 · ((P3(t) / P1(t))0.2857143-1) when P4(t) / P2(t) > 0.528 u2(t) = c · (5 · ((P3(t) / P1(t))0.2857143-1) when P4(t) / P2(t) > When P2(t) / P0≤0.528, u1(t)=c, c is the speed of sound; The acceleration a(t) of the overloading platform is: a(t) = 0.9N(P4(t) - P w )A0 / M where A0 is the cylinder piston area, A0 = πR0 2 , the mass of the overload platform M (kg); Pw is the cylinder friction force; The velocity increment v(t+dt) is: v(t+dt)=v(t)+a(t)dt The motion stroke S(t) of the cylinder is: S(t+dt)=v(t+dt)dt+0.5a(t+dt)dt^2+S(t) When the motion stroke S(t) of the cylinder is greater than or equal to L (in Table 1), the stroke of the cylinder ends, and the overloading platform stops moving. Wherein, the cylinder throttle hole radius R2(m); the cylinder radius R3(m); the cylinder stroke S(t)=L(m); the cylinder initial cavity V1m 3 .

6. A computer readable storage medium, characterized in that, The computer readable storage medium comprises a stored program, wherein the program performs the ground test method for simulating high overload separation of a rocket repeatedly as claimed in claim 5 when executed. 7.An electronic device comprising a memory and a processor, the electronic device characterized by, The memory stores a computer program, and the processor is configured to execute the ground test method for simulating high overload separation of a rocket repeatedly as claimed in claim 5 through the computer program.

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