Armored vehicle anti-recoil design method based on recoil fluid soft recoil

Abstract

The invention discloses an armored vehicle anti-recoil design method based on recoil fluid soft recoil, and relates to the technical field of recoil fluid soft recoil, and the method comprises the steps: constructing a recoil fluid soft recoil structure, and constructing a recoil fluid soft recoil launching motion model through the simulation processing of the launching process of the recoil fluid soft recoil structure; and according to the recoil fluid soft recoil launching motion model, establishing a recoil fluid soft recoil launching process total motion differential equation.

Description

Technical Field

[0001] The invention relates to the technical field of parking liquid soft recoil, and in particular to an armored vehicle anti-recoil design method based on parking liquid soft recoil. Background Art

[0002] At present, due to the common characteristics of high gun chamber pressure and short gun recoil distance in our army's main battle armored vehicles, large gun recoil is brought about. In order to reduce the adverse effects of gun recoil, relevant measures need to be taken to reduce the gun recoil, such as increasing the chassis load, but this will greatly reduce the mobility of armored vehicles. In the face of the ever-changing battlefield environment, the decline in mobility will not only make it easy for the enemy to detect and destroy it, but also easily miss favorable battlefield opportunities; at the same time, reducing the caliber of the gun to achieve the purpose of reducing recoil is obviously contrary to the improvement of firepower efficiency, which ultimately causes the firepower efficiency and mobility of armored vehicles to be in a state of mutual restriction for a long time. Therefore, it is urgent to adopt a complementary method, which does not reduce the caliber of the gun or even increase the caliber of the gun to enhance the firepower efficiency of the armored vehicle; and does not change the chassis structure and load of the armored vehicle, and even further reduces the chassis load of the armored vehicle to improve the mobility of the armored vehicle.

[0003] The anti-recoil device is composed of a recoil mechanism and a return mechanism. When the recoil of the gun generates kinetic energy, the recoil mechanism converts most of the recoil kinetic energy into the liquid in the recoil mechanism (recoil fluid) and the heat energy of the various parts of the recoil mechanism. As the temperature rises, it is finally dissipated into the surrounding atmosphere, thereby controlling the recoil movement of the gun; and the return mechanism stores a small amount of recoil kinetic energy generated by the recoil of the gun in a reversible form to ensure that the recoil part of the gun returns to the position before shooting. Obviously, the recoil mechanism plays an important role in reducing the recoil of the gun, especially the recoil fluid inside the recoil mechanism plays a key role in dissipating the heat energy generated by the recoil kinetic energy of the gun. In other words, whether the recoil fluid can work normally determines whether the recoil mechanism can maximize the role of reducing the recoil of the gun.

[0004] However, as the number of consecutive shots increases, the temperature of the recoil mechanism gradually rises, and the recoil fluid expands with the increase in temperature, reducing the space in the recoil mechanism except for the liquid, which may cause the recoil part to fail to return to its position. If the gun continues to shoot, the recoil movement law of the gun will change until the gun is damaged. Currently, the recoil fluid needs to be added manually, which increases maintenance costs. Summary of the invention

[0005] The invention provides an armored vehicle anti-recoil design method based on recoil fluid soft recoil, so as to solve the technical problem of how to reduce the recoil force of artillery.

[0006] The embodiment of the present invention provides a vehicle anti-squat design method based on parking fluid soft squat, comprising:

[0007] Constructing a recoil liquid soft recoil structure, and constructing a recoil liquid soft recoil launch motion model by simulating a launch process of the recoil liquid soft recoil structure;

[0008] According to the recoil liquid soft recoil launch motion model, a total motion differential equation of the recoil liquid soft recoil launch process is established.

[0009] Preferably, the total motion differential equation of the recoil liquid soft recoil launch process includes:

[0010]

[0011] Where, m represents the mass of the soft recoil part; F f Indicates the forward impact force; F φ Indicates the recoil force; F G represents the gravity component of the recoil part along the axis of the barrel; f represents the equivalent friction force of the recoil part, F pt Represents the resultant force in the barrel; sign(v) represents the direction of velocity v processed by the sign function.

[0012] Preferably, the forward impact force includes the forward impact force in the forward impact process, wherein the forward impact force in the forward impact process includes:

[0013] According to Bernoulli's equation, the pressure relationship expression during the forward thrust process is obtained;

[0014] By introducing the resistance coefficient and the continuity equation in the forward thrust process, the pressure relationship expression in the forward thrust process is solved to obtain the pressure at the piston rod of the forward thrust machine in the forward thrust process;

[0015] According to the pressure at the piston rod of the forward punch machine during the forward punch process and the working area of ​​the piston rod of the forward punch machine during the forward punch process, the forward impact force during the forward punch process is obtained.

[0016] Preferably, the forward impact force during the forward impact process includes:

[0017]

[0018] Among them, F f1 Indicates the forward impact force during the forward rush; A s1 Indicates the working area of ​​the piston rod of the forward punch during the forward punch process; p s1 Indicates the pressure at the piston rod of the forward thruster during the forward thrust process; p f01 Indicates the initial pressure of the gas in the forward thruster during the forward thrust process; V 01Indicates the initial volume of gas in the forward thruster during the forward thrust; A f1 represents the working area of ​​the floating piston of the forward thruster during the forward thrust; ρ1 represents the density of the gas in the forward thruster during the forward thrust; K f1 It represents the resistance coefficient during the forward thrust process; v1 represents the piston rod speed of the forward thrust machine during the forward thrust process.

[0019] Preferably, the recoil force includes the forward impact force during the forward rush, wherein the recoil force during the forward rush includes:

[0020] F Φ1 =127.09v1 2 +404.07v1

[0021] Among them, F Φ1 Indicates the recoil force during the forward thrust.

[0022] Preferably, the forward impact force also includes the forward impact force during the recoil process, and the forward impact force during the recoil process includes:

[0023] According to Bernoulli's equation, the pressure relationship expression during the recoil process is obtained;

[0024] By introducing the drag coefficient and the continuity equation during the sitting process, the pressure relationship expression during the recoil process is solved to obtain the pressure at the piston rod of the forward thruster during the sitting process;

[0025] The forward impact force during the recoil process is obtained according to the pressure at the piston rod of the forward thruster during the seating process and the working area of ​​the piston rod of the forward thruster during the seating process.

[0026] Preferably, the forward impact force during the recoil process includes:

[0027]

[0028] Among them, F f2 Indicates the forward impact force during the recoil process; A s2 Indicates the working area of ​​the piston rod of the forward thruster during the recoil process; p s2 Indicates the pressure at the piston rod of the forward thruster during the recoil process; p f02 Indicates the initial pressure of the gas in the forward engine during the recoil process; V 02 Indicates the initial volume of gas in the forward engine during the recoil process; A f2 represents the working area of ​​the floating piston of the front thruster during the recoil process; ρ2 represents the density of the gas in the front thruster during the recoil process; K f2 It represents the resistance coefficient during the recoil process; v2 represents the speed of the piston rod of the forward thruster during the recoil process.

[0029] Preferably, the recoil force also includes the recoil force during the recoil process, wherein the recoil force during the recoil process includes:

[0030]

[0031] Among them, F Φ2 Indicates the recoil force during the recoil process; Q 0 Indicates the total volume flow rate of the recoil brake fluid during the recoil process; K 1 Indicates the hydraulic resistance coefficient of the groove on the barrel wall of the recoil machine; K 2 Indicates the hydraulic resistance coefficient of the central flow port when the hydraulic channel of the recoil machine is divided into two types of channels; K 3 It indicates the resistance coefficient of the central flow channel when the hydraulic channel of the recoil machine changes from two types of channels to one type of channel; q 1 Indicates the volume flow rate of the groove on the barrel wall of the recoil machine; q 2 Indicates the volume flow rate of the center flow outlet of the recoil machine; u 3 Indicates the liquid flow rate in the groove of the barrel wall of the retreating machine; u 4 Indicates the liquid flow rate at the center flow port of the recoil machine; A x2 Indicates the center flow area of ​​the recoil brake piston; A 0 It represents the working area of ​​the recoil brake piston; ρ3 represents the gas density in the working chamber of the recoil brake during the recoil process; v3 represents the recoil speed during the recoil process.

[0032] The beneficial effects of the present invention are as follows: by constructing a recoil liquid soft recoil structure and simulating the firing process of the recoil liquid soft recoil structure, a recoil liquid soft recoil firing motion model is constructed; based on the recoil liquid soft recoil firing motion model, a total motion differential equation of the recoil liquid soft recoil firing process is established, thereby being able to reduce the recoil of the artillery, allowing the recoil liquid to achieve a dynamic adjustment mode based on actual needs, reducing the recoil of the vehicle under different conditions to a certain extent, thereby reducing the cost and weight of the vehicle platform, thereby reducing fuel and maintenance costs and enhancing the maneuverability of the vehicle. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 It is a flow chart of an armored vehicle anti-recoil design method based on recoil fluid soft recoil provided by the present invention;

[0034] Figure 2 It is a schematic diagram of Fluent dynamic mesh division provided by the present invention;

[0035] Figure 3 It is a schematic diagram of the forward impact resistance value of the recoil control machine provided by the present invention. DETAILED DESCRIPTION

[0036] It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention. In the subsequent description, the use of suffixes such as "module", "component" or "unit" used to represent elements is only to facilitate the description of the present invention and has no specific meaning in itself. Therefore, "module", "component" or "unit" can be used in a mixed manner.

[0037] Figure 1 Flow chart of a method for designing an armored vehicle recoil based on soft recoil of a recoil liquid provided by the present invention. Figure 1 As shown, including:

[0038] Step S101: constructing a recoil liquid soft recoil structure, and constructing a recoil liquid soft recoil launch motion model by simulating a launch process of the recoil liquid soft recoil structure;

[0039] Furthermore, the recoil liquid soft recoil structure at least includes a forward thruster and a recoil brake.

[0040] Step S102: According to the recoil liquid soft recoil launch motion model, a total motion differential equation of the recoil liquid soft recoil launch process is established.

[0041] In one embodiment of the present invention, the total motion differential equation of the recoil liquid soft recoil launch process includes:

[0042]

[0043] Where, m represents the mass of the soft recoil part; F f Indicates the forward impact force; F Φ Indicates the recoil force; F G represents the gravity component of the recoil part along the axis of the barrel; f represents the equivalent friction force of the recoil part, F pt Represents the resultant force in the barrel; sign(v) represents the direction of velocity v processed by the sign function.

[0044] Furthermore, during firing, the soft recoil portion is subjected to a forward force of 2F in the direction of the barrel axis. f , braking force F Φ , the equivalent friction force f on the recoil part, the gravity component F of the recoil part along the axis of the barrel G , the resultant force F pt The effect of equal forces. In the process of firing, the recoil part is taken as the research object, assuming that the directions of all forces act within the firing plane, and ignoring the effects of gaps, torques and elasticity at various locations, a simplified one-dimensional motion differential equation is established. A two-dimensional coordinate system is established with the muzzle direction as the positive direction and the card position as the zero point. Therefore, the total motion differential equation of the soft recoil firing process can be written as:

[0045]

[0046] Among them, F G =m h gsinθ, θ is the firing angle. Φ The direction of the equivalent friction force f is determined by the velocity direction, and its direction is processed using the sign function. f = μm h gcosθ, μ is the equivalent friction coefficient, m h The friction force includes the friction force at the cradle, the friction force at the seal of the forward punch and the recoil brake, and other friction forces.

[0047] In one embodiment of the present invention, the forward impact force includes the forward impact force during the forward impact process, wherein the forward impact force during the forward impact process includes:

[0048] According to Bernoulli's equation, the pressure relationship expression during the forward thrust process is obtained;

[0049] By introducing the resistance coefficient and the continuity equation in the forward thrust process, the pressure relationship expression in the forward thrust process is solved to obtain the pressure at the piston rod of the forward thrust machine in the forward thrust process;

[0050] According to the pressure at the piston rod of the forward punch machine during the forward punch process and the working area of ​​the piston rod of the forward punch machine during the forward punch process, the forward impact force during the forward punch process is obtained.

[0051] In one embodiment of the present invention, the forward impact force during the forward impact includes:

[0052]

[0053] Among them, F f1 Indicates the forward impact force during the forward rush; A s1 Indicates the working area of ​​the piston rod of the forward punch during the forward punch process; p s1 Indicates the pressure at the piston rod of the forward thruster during the forward thrust process; p f01 Indicates the initial pressure of the gas in the forward thruster during the forward thrust process; V 01 Indicates the initial volume of gas in the forward thruster during the forward thrust; A f1 represents the working area of ​​the floating piston of the forward thruster during the forward thrust; ρ1 represents the density of the gas in the forward thruster during the forward thrust; K f1 It represents the resistance coefficient during the forward thrust process; v1 represents the piston rod speed of the forward thrust machine during the forward thrust process.

[0054] Furthermore, the forward impact force during the forward impact (rebound) process is explained below:

[0055] Forward thrust machine force expression during forward thrust

[0056] The forward thruster uses the gas in the high-pressure gas chamber as the energy storage medium to push or absorb the energy of the piston rod outward. The changes in the high-pressure gas in the gas chamber can be described as a gas polymorphic process, that is.

[0057]

[0058] p f 、p f0 are the instantaneous pressure and initial pressure of the gas in the forward thruster, V and V 0 A is the instantaneous volume and initial volume of the gas, and n is the gas polynomial index. f A is the working area of ​​the floating piston, s is the working area of ​​the piston rod of the front punch, X 0 is the displacement of the floating piston, X is the displacement of the piston rod, which is numerically equal to the displacement of the recoil part, so the volume of the air cavity at any position is

[0059] V=V 0 -A f X 0

[0060] The liquid surface pressure of the moving piston is

[0061]

[0062] The following assumptions are often introduced when using the Bernoulli equation to calculate the characteristics of the recoil device: 1) the liquid is incompressible and the inner cavity is always filled with liquid; 2) the flow is a one-dimensional steady flow; 3) the earth is used as an inertial reference system; 4) the velocity and pressure of the liquid at a certain point are regarded as the average velocity and average pressure of the liquid on the cross section where the point is located. On this basis, the flow of the liquid in the recoil machine satisfies the continuity equation (mass conservation) and the Bernoulli equation (energy conservation). This assumption is applicable to the derivation of the Bernoulli equation in various places in the text.

[0063] The Bernoulli equation of the forward thrust machine is:

[0064]

[0065] In the formula, the pressure at the moving piston of the forward thruster is P f , pressure P at the piston rod s , w 1 is the flow rate of the liquid in the outer cylinder during the movement, w 2 is the flow rate of the liquid in the inner cylinder during the movement. Ignoring the height change of the center of the liquid flow, z q1 ≈z q2 , H f =ξ f w 2 2 / 2, and introduce the resistance coefficient K f =1+ξf , the continuity equation w 1 A f =w 2 A s , w 2 =v, substitute the above parameters into the above formula to solve for pressure P s ,have to

[0066]

[0067] Then the forward thrust process (v≥0) forward thrust force F f for:

[0068]

[0069] It should be noted that the forward impact force F f1 The expression of the forward thrust process (v ≥ 0) is the same as the forward thrust force F f The expression is the same expression, and its parameters have the same meaning.

[0070] In one embodiment of the present invention, the recoiling force includes the forward impact force during the forward rush, wherein the recoiling force during the forward rush includes:

[0071] F Φ1 =127.09v1 2 +404.07v1

[0072] Among them, F Φ1 Indicates the recoil force during the forward thrust.

[0073] Furthermore, the following is an explanation of the recoil force processing during the forward (return) process:

[0074] For the forward process, the liquid in the brake is used as the meshing object, the absolute pressure at the end face of the non-working chamber of the piston is set to 0, the standard k-ε turbulence model is applied to solve, and the dynamic mesh is updated in a layer-by-layer manner. The Fluent meshing is as follows: Figure 2 shown.

[0075] This fluid simulation uses the profile method to assign the motion velocity of the dynamic grid. The velocity data comes from the forward thrust velocity measured in the experiment. The simulation results of the forward thrust resistance value of the recoil brake are as follows: Figure 3 As shown. At a forward speed of 3m / s, the resistance of the recoil brake is only 2kN. The hydraulic resistance is much smaller than other forces in the whole process and has limited impact on the whole process. To simplify the calculation, a fitting equation is used to describe the force, which is treated as a quadratic equation about the piston rod speed v.

[0076] F Φ1 =127.09v1 2+404.07v1

[0077] In one embodiment of the present invention, the forward impact force also includes the forward impact force during the recoil process, and the forward impact force during the recoil process includes:

[0078] According to Bernoulli's equation, the pressure relationship expression during the recoil process is obtained;

[0079] By introducing the drag coefficient and the continuity equation during the sitting process, the pressure relationship expression during the recoil process is solved to obtain the pressure at the piston rod of the forward thruster during the sitting process;

[0080] The forward impact force during the recoil process is obtained according to the pressure at the piston rod of the forward thruster during the seating process and the working area of ​​the piston rod of the forward thruster during the seating process.

[0081] In one embodiment of the present invention, the forward impact force during the recoil process includes:

[0082]

[0083] Among them, F f2 Indicates the forward impact force during the recoil process; A s2 Indicates the working area of ​​the piston rod of the forward thruster during the recoil process; p s2 Indicates the pressure at the piston rod of the forward thruster during the recoil process; p f0 Indicates the initial pressure of the gas in the forward engine during the recoil process; V 02 Indicates the initial volume of gas in the forward engine during the recoil process; A f2 represents the working area of ​​the floating piston of the front thruster during the recoil process; ρ2 represents the density of the gas in the front thruster during the recoil process; K f2 It represents the resistance coefficient during the recoil process; v2 represents the speed of the piston rod of the forward thruster during the recoil process.

[0084] Furthermore, the forward impact force during the recoil process is explained below:

[0085] Recoil process forward thrust force expression

[0086] When the forward thruster is in the recoil process, the internal fluid flow direction and the forward thrust process (v≥0) forward thruster force F f In contrast, the pressure relationship during recoil is written according to Bernoulli's equation:

[0087]

[0088] The same forward thrust process (v≥0) is used for the above formula. f The parameter values ​​and simplified principles mentioned above make the forward thrust force F during the recoil process (v<0) f for:

[0089]

[0090] It should be noted that the forward impact force F during the aforementioned recoil process f2 The expression of the forward thrust F during the recoil process (v<0) f The expression is the same expression, and its parameters have the same meaning.

[0091] In one embodiment of the present invention, the recoil force also includes the recoil force during the recoil process, wherein the recoil force during the recoil process includes:

[0092]

[0093] Among them, F Φ2 Indicates the recoil force during the recoil process; Q 0 Indicates the total volume flow rate of the recoil brake fluid during the recoil process; K 1 Indicates the hydraulic resistance coefficient of the groove on the barrel wall of the recoil machine; K 2 Indicates the hydraulic resistance coefficient of the central flow port when the hydraulic channel of the recoil machine is divided into two types of channels; K 3 It indicates the resistance coefficient of the central flow channel when the hydraulic channel of the recoil machine changes from two types of channels to one type of channel; q 1 Indicates the volume flow rate of the groove on the barrel wall of the recoil machine; q 2 Indicates the volume flow rate of the center flow outlet of the recoil machine; u 3 Indicates the liquid flow rate in the groove of the barrel wall of the retreating machine; u 4 Indicates the liquid flow rate at the center flow port of the recoil machine; A x2 Indicates the center flow port area of ​​the recoil brake piston; A 0 It represents the working area of ​​the recoil brake piston; ρ3 represents the gas density in the working chamber of the recoil brake during the recoil process; v3 represents the recoil speed during the recoil process.

[0094] Furthermore, the braking force during the recoil process is explained below:

[0095] Recoil braking force expression

[0096] The small liquid flow hole A on the recoil machine piston is a fixed area liquid flow hole, and the 6 cylinder wall grooves are evenly distributed along the circumferential direction. The groove depth h = h (x) is a piecewise function, which changes continuously in the recoil machine axis direction, and the slope of each section is different. In theory, the change of groove depth will affect the size of the recoil machine force, and the appropriate groove depth can obtain a "gentle" recoil resistance.

[0097] For the liquid flow process, the continuity equation can be written as

[0098] A 0 v=Q0 =q 1 +q 2 =u 3 A x1 +u 4 A x2

[0099] In the formula, Q 0 is the total volume flow rate of the liquid, q 1 ,q 2 are the volume flow rates of the cylinder wall groove and the central flow port, A 0 A is the working area of ​​the recoil machine piston, x1 , A x2 are the groove area of ​​the cylinder wall and the flow port area of ​​the piston center, u 3 、u 4 are the liquid flow rates of the cylinder wall groove and the central flow port respectively. 1 With non-working cavity P 2 and considering the volume flow of the total flow and the split flow

[13] , the Bernoulli equation can be written as

[0100]

[0101] In the formula, H r1 and H r2 It is the specific energy loss of the liquid in the process of flowing from the working chamber to the non-working chamber, which is proportional to the specific kinetic energy, that is,

[0102]

[0103] Under the above assumptions, we can get u 1 =u 2 =0,P 2 = 0; ignore the height change of the flow center, z 1 ≈

[0104] z 2 , z 3 ≈z 4 , eliminate the equal terms, and then introduce K 1 =1+ξ 1 , K 2 =1+ξ 2 , simplified to

[0105]

[0106] Solving for P 1 Available

[0107]

[0108] K 1 , K2 are the hydraulic resistance coefficients of the cylinder wall groove and the center flow port respectively. Then the hydraulic resistance F of the recoil machine during the recoil process is Φ for

[0109]

[0110] In addition, since the grooves on the barrel wall of the retreating machine disappear at x = 0.07m, the liquid channel changes from two types of channels to one type of channel, that is, when x < 0.07m, A x1 = 0. Before and after this point, the flow field in the recoil machine changes. When x>0.07m, the resistance coefficient of the central flow channel of the recoil machine is K 2 ; When x < 0.07m, it is K 3 At the same time, the expression of the recoil brake force also changes. The expression of the second stage recoil brake force can be obtained from the Bernoulli equation. The derivation process is similar to the above process. Then the expression of the recoil brake force in the whole working stage is as follows

[0111]

[0112] It should be noted that the recoil force F during the aforementioned recoil process is Φ2 The expression of the full working section force of the brake is F Φ The expression is the same expression, and its parameters have the same meaning.

[0113] Among them, the hydraulic resistance coefficient K 1 The parameterization is as follows:

[0114] For the cylinder wall groove in the recoil machine, its cross-sectional area changes along the piston movement direction. In order to more accurately describe the recoil machine force and improve the description accuracy of the model, the cylinder wall groove hydraulic resistance coefficient K 1 is defined as a continuous variable. In order to meet the continuity requirement, the resistance coefficients corresponding to the four continuous cylinder wall grooves with different slopes are parameterized to provide an accurate model basis for parameter identification. Combined with the description of the hydraulic resistance coefficient in fluid mechanics, let K 1 The changing rule is

[0115]

[0116] When X>0.25, the cross-sectional area of ​​the groove on the cylinder wall is a constant, so K 1 =K c is a certain value. Under the constraints of this system of equations, K 1 The value range of is a subinterval of [1, C]. To meet the continuity requirement, the cross-sectional area value at the node is substituted and the b in the formula can be eliminated through mathematical processing. 1 , b 2 , that is, the hydraulic resistance coefficient K 1 It can be expressed asC , γ 1 , γ 2 The functional relationship of .

[0117] Similarly, the modeling of the buffer structure is similar to the above process and will not be repeated here.

[0118] The preferred embodiments of the present invention are described above with reference to the accompanying drawings, but the scope of the present invention is not limited thereby. Any modification, equivalent substitution and improvement made by those skilled in the art without departing from the scope and essence of the present invention shall be within the scope of the present invention.

Claims

1. A method for designing armored vehicle recoil based on soft recoil of a recoil liquid, characterized in that: include: Constructing a recoil liquid soft recoil structure, and constructing a recoil liquid soft recoil launch motion model by simulating a launch process of the recoil liquid soft recoil structure; According to the recoil liquid soft recoil launch motion model, a total motion differential equation of the recoil liquid soft recoil launch process is established.

2. The method according to claim 1, characterized in that The total motion differential equation of the recoil liquid soft recoil launch process includes: Where, m represents the mass of the soft recoil part; F f Indicates the forward impact force; F Φ Indicates the recoil force; F G represents the gravity component of the recoil part along the axis of the barrel; f represents the equivalent friction force of the recoil part, F pt Represents the resultant force in the barrel; sign(v) represents the direction of velocity v processed by the sign function.

3. The method according to claim 2, characterized in that The forward impact force includes the forward impact force during the forward impact process, wherein the forward impact force during the forward impact process includes: According to Bernoulli's equation, the pressure relationship expression during the forward thrust process is obtained; By introducing the resistance coefficient and the continuity equation in the forward thrust process, the pressure relationship expression in the forward thrust process is solved to obtain the pressure at the piston rod of the forward thrust machine in the forward thrust process; According to the pressure at the piston rod of the forward punch machine during the forward punch process and the working area of ​​the piston rod of the forward punch machine during the forward punch process, the forward impact force during the forward punch process is obtained.

4. The method according to claim 3, characterized in that The forward impact force in the forward impact process includes: Among them, F f1 Indicates the forward impact force during the forward rush; A s1 Indicates the working area of ​​the piston rod of the forward punch during the forward punch process; p s1 Indicates the pressure at the piston rod of the forward thruster during the forward thrust process; p f01 Indicates the initial pressure of the gas in the forward thruster during the forward thrust process; V 01 Indicates the initial volume of gas in the forward thruster during the forward thrust; A f1 represents the working area of ​​the floating piston of the forward thruster during the forward thrust; ρ1 represents the density of the gas in the forward thruster during the forward thrust; K f1 It represents the resistance coefficient during the forward thrust process; v1 represents the piston rod speed of the forward thrust machine during the forward thrust process.

5. The method according to claim 4, characterized in that The deceleration force includes the forward impact force during the forward rush, wherein the deceleration force during the forward rush includes: F φ1 =127.09v1 2 +404.07v1 Among them, F Φ1 Indicates the recoil force during the forward thrust.

6. The method according to claim 2, characterized in that The forward impact force also includes the forward impact force during the recoil process, and the forward impact force during the recoil process includes: According to Bernoulli's equation, the pressure relationship expression during the recoil process is obtained; By introducing the drag coefficient and the continuity equation during the sitting process, the pressure relationship expression during the recoil process is solved to obtain the pressure at the piston rod of the forward thruster during the sitting process; The forward impact force during the recoil process is obtained according to the pressure at the piston rod of the forward thruster during the seating process and the working area of ​​the piston rod of the forward thruster during the seating process.

7. The method according to claim 6, characterized in that The forward impact force during the recoil process includes: Among them, F f2 Indicates the forward impact force during the recoil process; A s2 Indicates the working area of ​​the piston rod of the forward thruster during the recoil process; p s2 Indicates the pressure at the piston rod of the forward thruster during the recoil process; p f02 Indicates the initial pressure of the gas in the forward engine during the recoil process; V 02 Indicates the initial volume of gas in the forward engine during the recoil process; A f2 represents the working area of ​​the floating piston of the front thruster during the recoil process; ρ2 represents the density of the gas in the front thruster during the recoil process; K f2 It represents the resistance coefficient during the recoil process; v2 represents the speed of the piston rod of the forward thruster during the recoil process.

8. The method according to claim 7, characterized in that The recoil force also includes the recoil force during the recoil process, wherein the recoil force during the recoil process includes: Among them, F Φ2 represents the force of the recoil machine during the recoil process; Q0 represents the total volume flow rate of the recoil machine liquid during the recoil process; K1 represents the hydraulic resistance coefficient of the groove on the barrel wall of the recoil machine; K2 represents the hydraulic resistance coefficient of the central flow port when the hydraulic channel of the recoil machine is two types of channels; K3 represents the resistance coefficient of the central flow channel when the hydraulic channel of the recoil machine changes from two types of channels to one type of channel; q1 represents the volume flow rate of the groove on the barrel wall of the recoil machine; q2 represents the volume flow rate of the central flow port of the recoil machine; u3 represents the liquid flow rate of the groove on the barrel wall of the recoil machine; u4 represents the liquid flow rate of the central flow port of the recoil machine; A x2 It represents the center flow port area of ​​the recoil brake piston; A0 represents the working area of ​​the recoil brake piston; ρ3 represents the gas density in the working chamber of the recoil brake during the recoil process; v3 represents the recoil speed during the recoil process.

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