# Study on the Fast Extension Mechanism of Double-Cavity Shock Absorber with High-Pressure Piston

Authors: Xingbo Fang; Hu Chen; Xiaohui Wei; Hong Nie
Journal: International Journal of Aerospace Engineering
 (2021)

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## Abstract

Double-cavity shock absorber with high-pressure piston is the core component of the nose landing gear of the carrier-based aircraft, and its fast-extension performance seriously affects the safety of the catapult-assisted takeoff. The design of a carrier-based aircraft in our country is carried out based on the traditional method of fast-extension dynamics, and it is found that the fast-extension capability is larger than designed. This paper analyzes the working principle of the high-pressure piston shock absorber and explains that the high-pressure air cavity pushes the piston rod to extend rapidly, which will cause the cavitation phenomenon in the main oil chamber. Thus, the cavitation in the main oil chamber makes the traditional modeling method of oil-liquid resistance force no longer applicable. Then, the axial force modeling method of shock absorber considering the cavitation effect is proposed. Based on the carrier-based aircraft, the dynamic response of the shock absorber in the process of fast extension is calculated and then it is compared with the calculation results of the traditional dynamic method. It is found that due to the cavitation effect caused by the forced fast extension section of the high-pressure air plug shock absorber, the fast extension work increases by 67.6%, thus, revealing the fast extension mechanism of the double-chamber shock absorber with high-pressure piston and successfully explaining the phenomenon of the fast extension ability exceeding the expectation of the shock absorber.


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## Body

## 1. Introduction

The shock absorber is the key component of the aircraft landing gear. For catapult carrier-based aircraft [1], the shock absorber should not only meet the landing shock absorber requirements of carrier-based aircraft but also the catapult fast-extension performance. Therefore, the double cavity shock absorber with high-pressure piston which can meet the above contradictory functional requirements is one of the common configurations of the nose landing gear of carrier-based aircraft.The dynamic characteristic analysis of the shock absorber is very important in the landing gear design. As early as 1951, Walls studied the parameter range of the variable index of air spring force [2] and contraction coefficient of oil hole [3] through the landing gear drop test. In 1976, Wahi studied the gas dissolution in the oil and the influence of oil compressibility on the dynamic characteristics of the shock absorber [4], and he also established a drop dynamic model including the dynamic characteristics of the shock absorber as well as the spin-up and spring back of the tire [5]. In 2009, Karam established the dynamic model of landing gear including the pressure of each cavity of shock absorber, the compressibility of oil, and the heat exchange between oil and gas [6], which has been verified by experiments. Chen et al. [7] found the abnormal fluctuation of vertical load in the landing gear drop test and judged that there was cavitation in the main oil chamber. Through theoretical calculation and laboratory test, it was proved that the existence of cavitation in the main oil chamber affects the landing gear shock absorber efficiency. Shin [8] used Adams to establish the dynamic model of single cavity shock absorber landing gear with cavitation effect, which proved that the simulation results were more consistent with the experimental results when the cavitation effect was taken into consideration.The internal structure of the double-chamber shock absorber with high-pressure piston is complex, and the dynamic process of its fast extension is in the backward stroke, which is obviously different from the landing shock absorber.Theoretical and experimental studies have been carried out on the dynamic characteristics of the nose landing gear of carrier-based aircraft. Shen and Huang [9] [10] established the dynamic model of fast extension of the dual cavity shock absorber of landing gear and optimized the oil needle section of the shock absorber. Liu and Li [11] obtained the landing gear double cavity shock absorber performance sample by ADAMS simulation analysis and established the surrogate model by using the nonlinear response surface method to optimize the landing gear dual cavity shock absorber performance. Zhang et al. [12] optimized the parameters of the landing gear dual cavity shock absorber by comprehensively considering the landing gear double cavity shock absorber’s landing shock absorber and fast-extension performance. Dou et al. [13] and Liu and Cui [14] carried out an experimental study on the fast extension process of landing gear with double cavity shock absorber, studied the influence of internal structure and filling parameters of shock absorber on the fast extension performance, and pointed out that the improvement of shock absorber performance would be accompanied by the decrease of shock absorber efficiency.In the above research on nose landing gear nose extension performance, the air spring force and oil damping force of shock absorber are modeled by traditional hydropneumatic shock absorber dynamics.The design of a carrier-based aircraft is carried out according to the traditional method of fast extension dynamics, and it is found that the fast extension capability is larger than designed. Based on the study of the working condition of each cavity of the high-pressure piston shock absorber, it is found that the negative pressure appears in the main oil chamber of the shock absorber during the fast extension process, resulting in the cavitation phenomenon, which leads to the invalidity of some assumptions in the modeling method of force elements such as oil resistance force in the traditional method of fast extension dynamics. Then, the dynamic pressure modeling method of each cavity in the shock absorber based on the elastic oil model is proposed, and the axial force calculation model of high-pressure air plug shock absorber considering the cavitation effect is established. Finally, the dynamic analysis of the nose landing gear fast extension process is carried out.


## 2. Working Principle of High-Pressure Air Plug Shock Absorber and Causes of Cavitation

The internal structure of the double chamber shock absorber with high-pressure piston is shown in Figure1(a). The shock absorber is mainly composed of high-pressure piston (1), piston retaining ring (2), side oil hole (3), main oil hole (4), and piston rod (5). Compared with the single chamber shock absorber shown in Figure 1(b), the shock absorber with high-pressure piston has added high-pressure piston and piston retaining ring. Each component of the shock absorber divides the internal space into four chambers, namely, high-pressure gas chamber (6), low-pressure gas chamber (7), side oil chamber (8), and main oil chamber (9). Compared with the single chamber shock absorber, high-pressure gas chamber is added.Figure 1
Structure diagram of shock absorber.
(a)(b)Figure2 shows the force analysis of shock absorber with high-pressure piston and conventional shock absorber in the piston extension. The compressed gas in the gas chamber of the conventional shock absorber (Figure 2(b)) compresses the oil in the gas chamber downward, and the oil flows to the main oil chamber through the main oil hole, squeezing the end face of the piston rod, so as to push the piston rod to extend outwards. In this process, the oil in the shock absorber remains squeezed, and there will be no negative pressure and cavitation. However, Figure 2(a) shows that there is a high-pressure gas cavity in the shock absorber of medium and high-pressure piston. The piston rod is directly squeezed through the high-pressure piston downward (forced fast extension) to push the piston rod to extend outward. Due to the high air pressure in the high-pressure air chamber, the piston rod extends and the volume of the main oil chamber increases rapidly. The flow of oil into the main oil chamber under the action of the pressure in the low-pressure chamber is not enough to fill the main oil chamber. Consequently, a negative pressure appears when the pressure of the main chamber drops, which causes the dissolved gas in the oil to expand and form cavitation.Figure 2
Force analysis of shock absorber.
(a)(b)


## 3. Traditional Modeling Method of Oil Damping Force and Its Problems

The traditional modeling method of the main oil hole resistance forceFoz of conventional hydropneumatic shock absorber is as follows.
(1)Foz=ρAoz32CdzAhz2ṡṡ,whereρ is oil density, Aoz is oil pressure area of main oil chamber, Cdz is shrinkage coefficient of main oil hole, Ahz is area of main oil hole, and s is compression capacity of shock absorber.When the shock absorber piston rod is extended,ṡ and Foz both are negative, then, the above formula can be arranged as follows.
(2)−CdzAhz−2ρFozAoz=Aozṡ.Meanwhile, according to the thin-walled hole flow algorithm [15], the flow formula of oil flowing through the shock absorber main oil hole during the piston rod extension can be written as follows:
(3)qz=−CdzAhz−2ρPz−Pd,whereqz represents the oil flow of the main oil hole (the flow from the main oil chamber to the low-pressure chamber is positive), Pd is the pressure of the low-pressure gas chamber, and Pz is the pressure of the main oil chamber.From the analogy between formulas (2) and (3), it can be concluded that the oil damping force in formula (1) can represent the force generated by the pressure difference on the main pressure oil area. The difference is caused by the flow rate corresponding to the volume change rate of the main oil chamber flowing through the main oil hole. Then, the premise of the modeling method in formula (1) is that the volume change rate of the main oil chamber is equal to the flow rate of the main oil hole.
(4)qz=Aozṡ.However, when cavitation occurs in the main oil chamber, as shown in Figure2(a), the cavitation occupies a part of the volume of the main oil chamber. According to the assumption of formula (4), the flow rate of the main oil hole is larger than the actual flow rate, so it can be concluded the oil damping force calculated by formula (1) is larger than the actual situation.


## 4. Axial Force Model of Shock Absorber considering Cavitation Effect

For the purpose of studying the influence of cavitation effect on the calculation results of reverse stroke axial force of the shock absorber with high-pressure piston, the following work has been carried out. Based on the principle of the shock absorber, the force analysis of the shock absorber piston rod was carried out, and the calculation model of axial force of shock absorber was established by dynamically calculating the pressure of each chamber in shock absorber considering cavitation effect.


### 4.1. Force Analysis of Shock Absorber Piston Rod

When the high-pressure piston shock absorber works in reverse stroke, it first goes through the high-pressure stroke condition, as shown in Figure3(a), and then goes through the low-pressure stroke condition, as shown in Figure 3(b). In Figure 3, the mechanical behaviors of piston rod in high-pressure stroke condition and low-pressure stroke condition are different. As a result, the axial force of shock absorber is calculated in low-pressure condition and high-pressure condition separately.
(5)Fh=Fhds≤sd,Fhgs>sd,Figure 3
Force analysis of piston rod.
(a)(b)wheresd is the stroke of shock absorber low-pressure structure.As shown in Figure3(a), during the high-pressure stroke condition, the piston rod is affected by the pressure of high-pressure gas chamber, low-pressure gas chamber, main oil chamber, and side oil chamber. The expression of resultant force along the axial direction of shock absorber is as follows.
(6)Fhg=Pg−PdAg+Pd−PcAd−Ah+PdAh−Az+PzAz,wherePg is the pressure of high-pressure gas chamber, Pd is the pressure of low-pressure gas chamber, Pz is the oil pressure of main oil chamber, Pc is the oil pressure of side oil chamber, Ag is the annular cross-sectional area of high-pressure piston, Ad is the cross-sectional area of low-pressure gas chamber, Az is the cross-sectional area of main oil chamber, and Ah is the external cross-sectional area of piston rod.The axial force on the piston rod during the low-pressure stroke condition of the shock absorber is shown in Figure3. The piston rod is separated from the high-pressure piston and only bears the pressure of the low-pressure gas chamber, main oil chamber, and side oil chamber. The expression of the shock absorber force on the piston rod is as follows.
(7)Fhd=Pd−PcAd−Ah+PdAh−Az+PzAz.


### 4.2. Calculation Model of Shock Absorber Chamber Pressure

The calculation error of traditional modeling method (1) of oil damping force lies in the assumption that the flow rate of main oil hole is equal to the volume change rate of main oil chamber. Taken the cavitation effect into consideration, the flow rate of main oil hole needs to be calculated by the pressure difference on both sides of oil hole. To calculate the oil hole flow, the internal pressure of each cavity should be calculated according to the dynamic state of oil elastic modulus.In equation (7), the calculation expression of the pressure in the low-pressure chamber is as follows.
(8)Pd=Pd0+PatmVd0Vd0+sgAg−sAd−Az−∫qz+qcγd−Patm,where the expression of high-pressure piston stroke is defined below.(9)sg=0s≤sd,s−sds>sd.In equation (6), the calculation expression of high-pressure gas chamber pressure is as follows.
(10)Pg=Pg0+PatmVg0Vg0−sgAgγg−Patm.In equation (7), without considering the elastic deformation of the piston rod, the expression of the time derivative of the oil pressure Pz in the main oil chamber is defined below.
(11)dPzdt=ṡAz−EzqzVz0−sAz,whereVz0 is the initial volume of the main oil chamber under the fully extended shock absorber state, Ez is the bulk modulus of the oil in the main oil chamber, and qz is the flow rate of the main oil chamber flowing to the low-pressure gas cavity through the main oil hole.The expression of oil bulk modulusE in oil chamber [15] is as follows.
(12)E=El1+αPatm/Patm+P1/γo1+αElPatm1/γo/γoPatm+Pγo+1/γo,whereEl is the bulk modulus of pure oil, α is the volume content of gas in the oil, γo is the polytropic index of gas in the oil, and P is the oil pressure in the oil chamber.In equation (7), the expression of the time derivative of the oil pressure in the side oil chamber is as follows.
(13)dPcdt=−ṡAc+EcqcVc0+sAc,whereVc0 is the initial volume of the side oil chamber, Ec is the volume modulus of the oil in the side oil chamber, and qc is the flow rate of the side oil cavity flowing to the low-pressure gas cavity through the side oil hole.


### 4.3. Flow Calculation Model of Damping Orifice

In equation (8), the expression of the flow rate of the main oil hole is as follows.
(14)qz=CdzAhzsignPz−Pd2Pz−Pdρ.In equation (11), the expression of side oil hole flow is as follows.
(15)qc=CdcAhcsignPc−Pd2Pc−Pdρ,whereCdc is the side oil hole shrinkage coefficient, and Ahc is the side oil hole area.


## 4.1. Force Analysis of Shock Absorber Piston Rod

When the high-pressure piston shock absorber works in reverse stroke, it first goes through the high-pressure stroke condition, as shown in Figure3(a), and then goes through the low-pressure stroke condition, as shown in Figure 3(b). In Figure 3, the mechanical behaviors of piston rod in high-pressure stroke condition and low-pressure stroke condition are different. As a result, the axial force of shock absorber is calculated in low-pressure condition and high-pressure condition separately.
(5)Fh=Fhds≤sd,Fhgs>sd,Figure 3
Force analysis of piston rod.
(a)(b)wheresd is the stroke of shock absorber low-pressure structure.As shown in Figure3(a), during the high-pressure stroke condition, the piston rod is affected by the pressure of high-pressure gas chamber, low-pressure gas chamber, main oil chamber, and side oil chamber. The expression of resultant force along the axial direction of shock absorber is as follows.
(6)Fhg=Pg−PdAg+Pd−PcAd−Ah+PdAh−Az+PzAz,wherePg is the pressure of high-pressure gas chamber, Pd is the pressure of low-pressure gas chamber, Pz is the oil pressure of main oil chamber, Pc is the oil pressure of side oil chamber, Ag is the annular cross-sectional area of high-pressure piston, Ad is the cross-sectional area of low-pressure gas chamber, Az is the cross-sectional area of main oil chamber, and Ah is the external cross-sectional area of piston rod.The axial force on the piston rod during the low-pressure stroke condition of the shock absorber is shown in Figure3. The piston rod is separated from the high-pressure piston and only bears the pressure of the low-pressure gas chamber, main oil chamber, and side oil chamber. The expression of the shock absorber force on the piston rod is as follows.
(7)Fhd=Pd−PcAd−Ah+PdAh−Az+PzAz.


## 4.2. Calculation Model of Shock Absorber Chamber Pressure

The calculation error of traditional modeling method (1) of oil damping force lies in the assumption that the flow rate of main oil hole is equal to the volume change rate of main oil chamber. Taken the cavitation effect into consideration, the flow rate of main oil hole needs to be calculated by the pressure difference on both sides of oil hole. To calculate the oil hole flow, the internal pressure of each cavity should be calculated according to the dynamic state of oil elastic modulus.In equation (7), the calculation expression of the pressure in the low-pressure chamber is as follows.
(8)Pd=Pd0+PatmVd0Vd0+sgAg−sAd−Az−∫qz+qcγd−Patm,where the expression of high-pressure piston stroke is defined below.(9)sg=0s≤sd,s−sds>sd.In equation (6), the calculation expression of high-pressure gas chamber pressure is as follows.
(10)Pg=Pg0+PatmVg0Vg0−sgAgγg−Patm.In equation (7), without considering the elastic deformation of the piston rod, the expression of the time derivative of the oil pressure Pz in the main oil chamber is defined below.
(11)dPzdt=ṡAz−EzqzVz0−sAz,whereVz0 is the initial volume of the main oil chamber under the fully extended shock absorber state, Ez is the bulk modulus of the oil in the main oil chamber, and qz is the flow rate of the main oil chamber flowing to the low-pressure gas cavity through the main oil hole.The expression of oil bulk modulusE in oil chamber [15] is as follows.
(12)E=El1+αPatm/Patm+P1/γo1+αElPatm1/γo/γoPatm+Pγo+1/γo,whereEl is the bulk modulus of pure oil, α is the volume content of gas in the oil, γo is the polytropic index of gas in the oil, and P is the oil pressure in the oil chamber.In equation (7), the expression of the time derivative of the oil pressure in the side oil chamber is as follows.
(13)dPcdt=−ṡAc+EcqcVc0+sAc,whereVc0 is the initial volume of the side oil chamber, Ec is the volume modulus of the oil in the side oil chamber, and qc is the flow rate of the side oil cavity flowing to the low-pressure gas cavity through the side oil hole.


## 4.3. Flow Calculation Model of Damping Orifice

In equation (8), the expression of the flow rate of the main oil hole is as follows.
(14)qz=CdzAhzsignPz−Pd2Pz−Pdρ.In equation (11), the expression of side oil hole flow is as follows.
(15)qc=CdcAhcsignPc−Pd2Pc−Pdρ,whereCdc is the side oil hole shrinkage coefficient, and Ahc is the side oil hole area.


## 5. Analysis of Dynamic Response Results of Shock Absorber during Fast Extension

Based on the test method of nose landing gear in reference [13], this paper studies the fast extension performance of nose landing gear shock absorber with high-pressure air plug.


### 5.1. Dynamic Model of Nose Landing Gear Extension

The dynamic model of nose landing gear nose extension test method is modeled by two mass models [14]. Take the basket, counterweight, landing gear strut and strut as elastic mass, and shock absorber piston rod, wheel, and tire as inelastic mass. The dynamic equation is as follows.
(16)mtxy¨tx=Fh−mtxg,mfty¨ft=−kvyft−Fh−mftg,wheremtx is the elastic support mass, mft is the inelastic support mass, ytx is the elastic mass vertical displacement, kv is the tire radial stiffness, yft is the inelastic mass vertical displacement, and g is the gravity acceleration.The dynamic response model is used to calculate the dynamic response of the nose landing gear of a carrier-based aircraft in the fast extension. The total structural stroke of the nose landing gear shock absorber of the carrier-based aircraft is 550 mm, and the structural stroke of the low pressure is 350 mm. At the initial moment of nose landing gear extension, the shock absorber compression is 478 mm. The specific model parameters are shown in Table1.Table 1
Simulation parameters.
SymbolValueSymbolValuesd350 mmPd00.5 MPasmax550 mmPg05.5 MPamft120 kgkv1.7e6 N/mmtx3360 kgVd03600 mLs0478 mmVg01040 mLg9.82 m/s2


### 5.2. Calculation Results of Axial Force Component of Shock Absorber (Traditional Modeling Method)

Figures4 and 5 show the oil resistance force Foz of main oil hole, air spring force Fad of low-pressure air chamber, and air spring force Fag of high-pressure air chamber in the process of fast extension using the traditional modeling method. The nose landing gear starts to extend at the zero point of the time axis. During the process of extension, the maximum reverse force Foz of shock absorber is 52.5 kN at the time 0.091 s, and the corresponding Fad value at this time is only 19.2 kN.Figure 4
Time history of axial component force.Figure 5
Time history of high-pressure cavity force.According to the principle of oil resistance force of main oil hole, in the process of shock absorber elongation, the reverse damping force of main oil hole is generated when oil flows from low-pressure chamber through main oil hole to main oil chamber. As a result, the value of reverse damping force of main oil hole shall not be greater than that of air spring force of low-pressure chamber. From this, we can see that the results of main oil hole reverse damping force and low-pressure chamber air spring force are contradictory. The reason is that the damping force of the main oil hole is not produced by air spring force of high-pressure chamber at 45.1 kN (Figure5), while the damping force is considered by traditional modeling method.


### 5.3. Comparison of Dynamic Response Calculation Results of Two Axial Force Models

Figure6 shows the pressure change of each shock absorber chamber during the fast extension process calculated by the shock absorber model considering cavitation effect. From the pressure curve of the main oil chamber in the figure, the pressure in the main oil chamber has been negative after 0.053 seconds, which indicates that cavitation has been existing in the main oil chamber after 0.053 s.Figure 6
Cavity pressure of shock absorber.The comparison results of the axial stroke of the shock absorber calculated by two modeling methods of the nose landing gear during extension are given in Figure7. It can be seen that there is obvious difference between the traditional modeling method and the shock absorber model with cavitation effect. The shock absorber model with cavitation effect reaches the fast extension at 0.1 s. However, it takes 0.130 s for the traditional modeling method to complete the high-pressure stroke. Moreover, due to the cavitation effect, the damping force of the main oil hole in the high-pressure stroke stage is invalid. The axial force calculated by the shock absorber model considering the cavitation effect is larger than that calculated by the traditional modeling method, and the work diagram of the shock absorber is also fuller (Figure 8). In Figure 8, the output work of the shock absorber model with cavitation effect is 9.05 kJ, while that of the shock absorber model with traditional modeling method is 5.40 kJ, with a difference of 67.6%.Figure 7
Comparison of shock strut stroke.Figure 8
Comparison of efficiency diagrams.In Figure8, when the shock absorber is in the low-pressure stroke stage (s<350mm), there is no obvious difference in the axial direction calculated by the two modeling methods. The reason is that the working principle of the high-pressure piston shock absorber in the low-pressure stroke stage is not significantly different from that of the conventional single cavity shock absorber. It reveals that the traditional modeling method of oil damping force is accurate for the calculation of single cavity shock absorber.Figure9 shows the vertical velocity of elastic support mass during nose landing gear fast extension. The peak velocity value calculated by shock absorber model with cavitation effect is 2.20 m/s, while that calculated by traditional modeling method is 2.07 m/s, with a difference of 6.3%. At the same time, there are also obvious differences in the vertical displacement calculated by the two shock absorber modeling methods (Figure 10). At the time of 0.3 s, the elastic support mass displacement value calculated by the shock absorber model considering the cavitation effect is 416.5 mm, while that calculated by the traditional modeling method is 338.0 mm, with a difference of 23.2%.Figure 9
Comparison of vertical velocity of spring support mass.Figure 10
Comparison of vertical displacement of spring support mass.


## 5.1. Dynamic Model of Nose Landing Gear Extension

The dynamic model of nose landing gear nose extension test method is modeled by two mass models [14]. Take the basket, counterweight, landing gear strut and strut as elastic mass, and shock absorber piston rod, wheel, and tire as inelastic mass. The dynamic equation is as follows.
(16)mtxy¨tx=Fh−mtxg,mfty¨ft=−kvyft−Fh−mftg,wheremtx is the elastic support mass, mft is the inelastic support mass, ytx is the elastic mass vertical displacement, kv is the tire radial stiffness, yft is the inelastic mass vertical displacement, and g is the gravity acceleration.The dynamic response model is used to calculate the dynamic response of the nose landing gear of a carrier-based aircraft in the fast extension. The total structural stroke of the nose landing gear shock absorber of the carrier-based aircraft is 550 mm, and the structural stroke of the low pressure is 350 mm. At the initial moment of nose landing gear extension, the shock absorber compression is 478 mm. The specific model parameters are shown in Table1.Table 1
Simulation parameters.
SymbolValueSymbolValuesd350 mmPd00.5 MPasmax550 mmPg05.5 MPamft120 kgkv1.7e6 N/mmtx3360 kgVd03600 mLs0478 mmVg01040 mLg9.82 m/s2


## 5.2. Calculation Results of Axial Force Component of Shock Absorber (Traditional Modeling Method)

Figures4 and 5 show the oil resistance force Foz of main oil hole, air spring force Fad of low-pressure air chamber, and air spring force Fag of high-pressure air chamber in the process of fast extension using the traditional modeling method. The nose landing gear starts to extend at the zero point of the time axis. During the process of extension, the maximum reverse force Foz of shock absorber is 52.5 kN at the time 0.091 s, and the corresponding Fad value at this time is only 19.2 kN.Figure 4
Time history of axial component force.Figure 5
Time history of high-pressure cavity force.According to the principle of oil resistance force of main oil hole, in the process of shock absorber elongation, the reverse damping force of main oil hole is generated when oil flows from low-pressure chamber through main oil hole to main oil chamber. As a result, the value of reverse damping force of main oil hole shall not be greater than that of air spring force of low-pressure chamber. From this, we can see that the results of main oil hole reverse damping force and low-pressure chamber air spring force are contradictory. The reason is that the damping force of the main oil hole is not produced by air spring force of high-pressure chamber at 45.1 kN (Figure5), while the damping force is considered by traditional modeling method.


## 5.3. Comparison of Dynamic Response Calculation Results of Two Axial Force Models

Figure6 shows the pressure change of each shock absorber chamber during the fast extension process calculated by the shock absorber model considering cavitation effect. From the pressure curve of the main oil chamber in the figure, the pressure in the main oil chamber has been negative after 0.053 seconds, which indicates that cavitation has been existing in the main oil chamber after 0.053 s.Figure 6
Cavity pressure of shock absorber.The comparison results of the axial stroke of the shock absorber calculated by two modeling methods of the nose landing gear during extension are given in Figure7. It can be seen that there is obvious difference between the traditional modeling method and the shock absorber model with cavitation effect. The shock absorber model with cavitation effect reaches the fast extension at 0.1 s. However, it takes 0.130 s for the traditional modeling method to complete the high-pressure stroke. Moreover, due to the cavitation effect, the damping force of the main oil hole in the high-pressure stroke stage is invalid. The axial force calculated by the shock absorber model considering the cavitation effect is larger than that calculated by the traditional modeling method, and the work diagram of the shock absorber is also fuller (Figure 8). In Figure 8, the output work of the shock absorber model with cavitation effect is 9.05 kJ, while that of the shock absorber model with traditional modeling method is 5.40 kJ, with a difference of 67.6%.Figure 7
Comparison of shock strut stroke.Figure 8
Comparison of efficiency diagrams.In Figure8, when the shock absorber is in the low-pressure stroke stage (s<350mm), there is no obvious difference in the axial direction calculated by the two modeling methods. The reason is that the working principle of the high-pressure piston shock absorber in the low-pressure stroke stage is not significantly different from that of the conventional single cavity shock absorber. It reveals that the traditional modeling method of oil damping force is accurate for the calculation of single cavity shock absorber.Figure9 shows the vertical velocity of elastic support mass during nose landing gear fast extension. The peak velocity value calculated by shock absorber model with cavitation effect is 2.20 m/s, while that calculated by traditional modeling method is 2.07 m/s, with a difference of 6.3%. At the same time, there are also obvious differences in the vertical displacement calculated by the two shock absorber modeling methods (Figure 10). At the time of 0.3 s, the elastic support mass displacement value calculated by the shock absorber model considering the cavitation effect is 416.5 mm, while that calculated by the traditional modeling method is 338.0 mm, with a difference of 23.2%.Figure 9
Comparison of vertical velocity of spring support mass.Figure 10
Comparison of vertical displacement of spring support mass.


## 6. Conclusions

(1)
It is concluded that for the shock absorber with high-pressure piston, in the forced fast extension condition, the high-pressure air cavity pushes the piston rod to extend rapidly, which will cause the main oil chamber to appear negative pressure and lead to cavitation(2)
It is clarified that cavitation in the main oil chamber of the shock absorber high-pressure piston will lead to the hypothesis that the volume change rate of the main oil chamber is equal to the flow rate of the main oil hole, which is the premise of the traditional oil damping force modeling method for sudden extension dynamics(3)
Based on the elastic oil model, the dynamic pressure modeling method of each chamber in the shock absorber is proposed, and the axial force model considering cavitation effect is established to calculate the dynamic pressure change in each chamber(4)
Based on the study of the dynamics of the shock absorber axial force modeling method considering the cavitation effect, it is found that compared with the traditional modeling method, the output work of the fast extension is increased by 67.6%



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