CN104217060B - A kind of undercarriage and pintle dynamic loading coupling analytical method - Google Patents

Abstract

The invention belongs to fixed wing airplane technical field is and in particular to arrive fixed wing airplane undercarriage and pintle dynamic loading coupling analytical method.It is characterized in that, based on overall aircraft landing configuration, geometric layout parameter, set up undercarriage, pintle kinesiology/kinetics equation, lower ginseng iteration by the Parametric designing of oil-gas type antivibrator and software environment to review, complete multi-body dynamics modeling and the numeric value analysis work of multiple subsystem such as aircraft pintle and undercarriage.Calculate assembled state each subsystem load, vibration reciprocal effect, realize Coupling Research.Analysis the load steady-state component of a certain subsystem, dynamic component under coupling condition, and compare with the dynamic loading analog reslt of released state, discrimination diversity and sensitive parameter, provide coupling/uncoupling and close research method, and pintle vibration and front, the vibration of main landing gear load avoidance method for designing of avoiding the peak hour.

Description

A kind of undercarriage and pintle dynamic loading coupling analytical method

Technical field

The invention belongs to fixed wing airplane technical field is and in particular to arrive fixed wing airplane undercarriage and pintle dynamic loading coupling Close analysis method.

Background technology

Fixed wing airplane undercarriage is aircraft body structure intensity key technology with the analysis of pintle dynamic loading.Conventional fixation Wing aircraft undercarriage and pintle dynamic loading analysis method, all with isolated monomer structure as object of study, do not fully take into account each Dynamic loading reciprocal effect effect between monomer structure, and to make substituting static research with empirical algorithms it follows that Result of calculation often false or too conservative.

Set up undercarriage and pintle dynamic loading coupling analytical method, carry out undercarriage and pintle dynamic loading coupling analysis, with This is as the characteristic foundation evaluating aircraft structural integrity, in this sense, the only undercarriage of voucher body or pintle Study of dynamic load is difficult to cover the use characteristic of aircraft.

It is contemplated that the drawbacks of dispel above-mentioned separation property research method, calculate assembled state each subsystem load, vibration Reciprocal effect, realizes Coupling Research.Analysis the load steady-state component of a certain subsystem, dynamic component under coupling condition, and with The dynamic loading analog reslt of released state is compared, discrimination diversity and sensitive parameter, provides coupling/uncoupling and closes research Method, and pintle vibration and front, the vibration of main landing gear load avoidance method for designing of avoiding the peak hour.

Content of the invention

The present invention is based on overall aircraft weight configuration, geometric layout parameter it is established that the frame that falls, pintle kinesiology/kinetics Equation, lowers ginseng iteration by the Parametric designing of oil-gas type antivibrator and software environment and reviews, complete aircraft pintle and rise and fall The multi-body dynamics modeling of multiple subsystem such as frame and numeric value analysis work.

The technical scheme is that：A kind of undercarriage and pintle dynamic loading coupling analytical method it is characterised in that Comprise the steps：

1. a kind of undercarriage and pintle dynamic loading coupling analytical method it is characterised in that：

First, set up the equilibrium equation of full machine power and the equilibrium equation of moment：

In two above equation group, m is Aircraft Quality, and I is aircraft rotary inertia；V is aircraft linear velocity, and a is aircraft line Acceleration；ω is aircraft angular velocity, and ε is aircraft angular acceleration；F is the external force of aircraft, and M is the moment of face of aircraft；Subscript x, Y, z characterize three direction in spaces of airplane motion.

Second, set up undercarriage and pintle dynamic loading coupled wave equation：

In two above equation group, m is Aircraft Quality（Measured value）, I is aircraft rotary inertia（Measured value）；V is aircraft Linear velocity（Measured value）, a is aircraft linear acceleration（Measured value）；ω is aircraft angular velocity（Measured value）, ε is aircraft angular acceleration （Measured value）；F is the external force of aircraft（Measured value）, M is the moment of face of aircraft（Measured value）；T is time variable；Subscript x, y, Z characterizes three direction in spaces of airplane motion；Subscript NLG characterizes nose-gear, and subscript MLG characterizes main landing gear, inferior horn Mark AH characterizes pintle, and subscript L characterizes lift, and subscript D characterizes resistance, and subscript T characterizes motor power.

3rd, decoupling equation, obtain the stand under load of monomer structure.

After undercarriage and pintle dynamic loading coupling analytical method are set up and are completed combination calculation analysis, Ke Yitong Cross the stand under load that output result isolates monomer structure, design offer fatigue resistance assumed (specified) load for monomer structure, thus realizing " coupling → decoupling " reverse process.

By shake to check cable vibration frequency during aircraft arrestment, stress wave energy transmission and with aircraft body structure The analytical technology research of dynamic coupling response, during formation aircraft arrestment, undercarriage shock wave and pintle shock wave are to body The dynamic response analysis method of structure, identification undercarriage, the dynamic loading frequency of pintle Oscillatory Coupling, amplitude and time history etc. respectively Key parameter, sets up the coupling analysis technology of stress wave energy transmission and aircaft configuration shock response.

The present invention calculates assembled state each subsystem load, vibration reciprocal effect, realizes Coupling Research, and this is as evaluation The characteristic foundation of aircraft structural integrity, provides coupling/uncoupling and closes research method, and pintle vibration and front, main landing gear The avoidance method for designing of avoiding the peak hour of load vibration.

Each parameter of being related to of formula calculating in the present invention, a part flies ginseng recording equipment by aircraft airborne to be provided, such as quality, Rotary inertia, speed, acceleration, power and moment；Another part is derived from the real time data of motion platform arresting system, such as blocks Power.

It is an advantage of the invention that：

1）Under the constraint based on landing gear of aircraft Structural Strength Design integrated design principle for the present invention, using the solid coupling of stream Rationally discuss, performance optimization and structural design optimization can be made synchronously to carry out.Meanwhile, by introducing avoidance design concept of avoiding the peak hour, by tail Hook, main landing gear, the time phase difference of the load peaks of the big key landing structure of nose-gear three control within preset range.

2）Using analysis method of the present invention, aircraft can be tracked whole landing, the process of blocking, and draw and describe The parameter curve of dropping control device dynamic property, whether the design parameter of analysis whole system meets design requirement, is the debugging of system Select to provide foundation with parameter, thus shortening research cycle, also so that for the further investigation of system and physics actual loading test more Tool safety and reliability.

3）Using analysis method of the present invention, can complete to take off, land, block, sliding and run the undercarriage of operating mode and the tails such as obstacle detouring Hook dynamic loading coupling analysis.Optimize the design cushion system parameter providing undercarriage, pintle, completion system overall performance reasonability Assessment report is it is ensured that static strength qualification test, fatigue resistance qualification test pass through.

Brief description

Fig. 1 is undercarriage and pintle dynamic loading coupling analytical method figure.

Fig. 2 undercarriage monosomic analysises method figure.

Specific embodiment

Below by specific embodiment and combine accompanying drawing the present invention is described in further detail.

Certain type fixed wing airplane, its Landing gear original calculation known parameters is

In above-mentioned parameter, m is Aircraft Quality（Measured value）, I is aircraft rotary inertia（Measured value）；V is aircraft linear velocity （Measured value）, a is aircraft linear acceleration（Measured value）；ω is aircraft angular velocity（Measured value）, ε is aircraft angular acceleration（Actual measurement Value）；L is lift（Measured value）, D is resistance（Measured value）, T is motor power（Measured value）.Subscript x, y, z characterizes aircraft Three direction in spaces of motion.

Based on the inventive method, using Dynamics Simulation Analysis software platform, complete modeling, debugging and computer sim- ulation work Make, it is achieved that " coupling → decoupling " calculates, to draw：

Nose-gear load is

Main landing gear load is

Pintle load is

Wherein, F is undercarriage and pintle load, and unit is N；Subscript x, y, z characterizes three space sides of airplane motion To；Subscript NLG characterizes nose-gear, and subscript MLG characterizes main landing gear, and subscript AH characterizes pintle.

Claims (1)

1. a kind of undercarriage and pintle dynamic loading coupling analytical method are it is characterised in that comprise the steps：

First, set up the equilibrium equation of full machine power and the equilibrium equation of moment：

$\begin{array}{cc}\left\{\begin{array}{c}m\·(a_x+{\mathrm{\ω}}_y\·v_z-{\mathrm{\ω}}_z\·v_y)=\ΣF_x\\ m\·(a_y+{\mathrm{\ω}}_z\·v_x-{\mathrm{\ω}}_x\·v_z)=\ΣF_y\\ m\·(a_z+{\mathrm{\ω}}_x\·v_y-{\mathrm{\ω}}_y\·v_x)=\ΣF_x\end{array}\right.& \left\{\begin{array}{c}{I}_x\·{\mathrm{\ϵ}}_x-(I_y-I_z)\·{\mathrm{\ω}}_y\·{\mathrm{\ω}}_z={\mathrm{\ΣM}}_x\\ I_y\·{\mathrm{\ϵ}}_y-(I_z-I_x)\·{\mathrm{\ω}}_z\·{\mathrm{\ω}}_x={\mathrm{\ΣM}}_y\\ I_z\·{\mathrm{\ϵ}}_z-(I_x-I_y)\·{\mathrm{\ω}}_x\·{\mathrm{\ω}}_y={\mathrm{\ΣM}}_z\end{array}\right.\end{array}$

In two above equation group, m is Aircraft Quality, and I is aircraft rotary inertia；V is aircraft linear velocity, and a accelerates for aircraft line Degree；ω is aircraft angular velocity, and ε is aircraft angular acceleration；F is the external force of aircraft, and M is the moment of face of aircraft；Subscript x, y, z table Levy three direction in spaces of airplane motion；

Second, set up undercarriage and pintle dynamic loading coupled wave equation：

$\left\{\begin{array}{c}m\·\[a_x\left(t\right)+{\mathrm{\ω}}_y\left(t\right)\·v_z\left(t\right)-{\mathrm{\ω}}_z\left(t\right)\·v_y\left(t\right)\]=F_{x.NLG}\left(t\right)+F_{x.MLG}\left(t\right)+F_{x.AH}\left(t\right)+F_{x.T}\left(t\right)+F_{x.D}\left(t\right)\\ m\·\[a_y\left(t\right)+{\mathrm{\ω}}_z\left(t\right)\·v_x\left(t\right)-{\mathrm{\ω}}_x\left(t\right)\·v_z\left(t\right)\]=F_{y.NLG}\left(t\right)+F_{y.MLG}\left(t\right)+F_{y.AH}\left(t\right)+F_{y.L}\left(t\right)\\ m\·\[a_z\left(t\right)+{\mathrm{\ω}}_x\left(t\right)\·v_y\left(t\right)-{\mathrm{\ω}}_y\left(t\right)\·v_x\left(t\right)\]=F_{z.NLG}\left(t\right)+F_{z.MLG}\left(t\right)+F_{z.AH}\left(t\right)\end{array}\right.$

$\left\{\begin{array}{c}{I}_x\·{\mathrm{\ϵ}}_x\left(t\right)-(I_y-I_z)\·{\mathrm{\ω}}_y\left(t\right)\·{\mathrm{\ω}}_z\left(t\right)=M_{x.NLG}\left(t\right)+M_{x.MLG}\left(t\right)+M_{x.AH}\left(t\right)\\ I_y\·{\mathrm{\ϵ}}_y\left(t\right)-(I_z-I_x)\·{\mathrm{\ω}}_z\left(t\right)\·{\mathrm{\ω}}_x\left(t\right)=M_{y.NLG}\left(t\right)+M_{y.MLG}\left(t\right)+M_{y.AH}\left(t\right)\\ I_z\·{\mathrm{\ϵ}}_z\left(t\right)-(I_x-I_y)\·{\mathrm{\ω}}_x\left(t\right)\·{\mathrm{\ω}}_y\left(t\right)=M_{z.NLG}\left(t\right)+M_{z.MLG}\left(t\right)+M_{z.AH}\left(t\right)+M_{z.T}\left(t\right)+M_{z.L}\left(t\right)+M_{z.D}\left(t\right)\end{array}\right.$

In two above equation group, m is Aircraft Quality, and I is aircraft rotary inertia；V is aircraft linear velocity, and a accelerates for aircraft line Degree；ω is aircraft angular velocity, and ε is aircraft angular acceleration；F is the external force of aircraft, and M is the moment of face of aircraft；T is the time；Inferior horn Mark x, y, z characterizes three direction in spaces of airplane motion；Subscript NLG characterizes nose-gear, and subscript MLG characterizes master and rises and falls Frame, subscript AH characterizes pintle, and subscript L characterizes lift, and subscript D characterizes resistance, and subscript T characterizes motor power；

3rd, decoupling equation, obtain the stand under load of monomer structure

After undercarriage and pintle dynamic loading coupling analytical method are set up and completed combination calculation analysis, tied by output Fruit isolates the stand under load of monomer structure, designs offer fatigue resistance assumed (specified) load for monomer structure, thus realizing " coupling → decoupling The reverse process of conjunction ".