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1.
A scheme is proposed, of that the axis of directional barrel is simulated by a laser beam and an electro-optical axial angle encoder is using to measure the swaying of rocket launcher or artillery. The measuring principle is stated, and an electro-optical measuring system is designed, including automatic force-applying device, angle-measurement device and photodetecting screen. The measurement accuracy of the system is analyzed. The measuring error of system is less then 17.3"(0.08 mil).  相似文献   

2.
In order to explore the rules of the deformation force during the launching of a small-diameter steel cartridge, the semi-closed bomb test method is used to test the greatest strains on chamber outer wall under the different chamber pressures. The pressure curves of cartridge chamber are measured in experiment, and the tensile test data of cartridge are loaded into the numerical calculation to compare with the experimental data. The conclusion was obtained that the calculated results match better with the experimental results by considering strain rate bilinear kinematic hardening material constitutive model. The forces on the various parts of the cartridge during launching and their deformation rules are achieved, in which the equivalent plastic strain decreases and the cylinder ring withstands the maximum equivalent stress when the cartridge case clings to the bore from the mouth to the bottom.  相似文献   

3.
An adaptive backstepping sliding mode control approach is introduced to control the pitch motion of a rocket launcher. Its control law is proposed to guarantee that the control system is ultimately bounded in a Lyapunov sense and make the servo system track the instruction of reference position globally and asymptotically. In addition, the sliding mode control can restrain the effects of parameter uncertainties and external disturbance. The functions of adaptive mechanism and sliding mode control are analyzed through the simulation in the different conditions.The simulation results illustrate that the method is applicable and robust.  相似文献   

4.
The reliability of the electronic components inside a guided projectile is highly affected by the launch dynamics of guided projectile. The engraving process plays a crucial role on determining the ballistic performance and projectile stability. This paper analyzes the dynamic response of a guided projectile during the engraving process. By considering the projectile center of gravity moving during the engraving process, a dynamics model is established with the coupling of interior ballistic equations. The results detail the stress situation of a guided projectile band during its engraving process. Meanwhile, the axial dynamic response of projectile in the several milliseconds following the engraving process is also researched. To further explore how the different performance of the engraving band can affect the dynamics of guided projectile, this paper focuses on these two aspects: (a) the effects caused by the different band geometry; and (b) the effects caused by different band materials. The time domain and frequency domain responses show that the dynamics of the projectile are quite sensitive to the engraving band width. A material with a small modulus of elasticity is more stable than one with a high modulus of elasticity.  相似文献   

5.
A flight control system is designed for a reusable launch vehicle with aerodynamic control surfaces and reaction control system based on a variable-structure control and neural network theory.The control problems of coupling among the channels and the uncertainty of model parameters are solved by using the method.High precise and robust tracking of required attitude angles can be achieved in complicated air space.A mathematical model of reusable launch vehicle is presented first,and then a controller of flight system is presented.Base on the mathematical model,the controller is divided into two parts:variable-structure controller and neural network module which is used to modify the parameters of controller.This control system decouples the lateraldirectional tunnels well with a neural network sliding mode controller and provides a robust and de-coupled tracking for mission angle profiles.After this a control allocation algorithm is employed to allocate the torque moments to aerodynamic control surfaces and thrusters.The final simulation shows that the control system has a good accurate,robust and de-coupled tracking performance.The stable state error is less than 1°,and the overshoot is less than 5%.  相似文献   

6.
In order to measure the instantaneous thrust of a certain attitude-control solid rocket motor, based on the analysis of the measurement principles, the difference between the instantaneous thrust and steady thrust measurements is pointed out. According to the measurement characteristics, a dynamic digital filter compensation method is presented. Combined the identification-modeling, dynamic compensation and simulation, the system's dynamic mathematic model is established. And then, a compensation digital filter is also designed. Thus, the dynamic response of the system is improved and the instantaneous thrust measurement can be implemented. The measurement results for the rocket motor show that the digital filter compensation is effective in the instantaneous thrust measurement.  相似文献   

7.
8.
An attitude control algorithm for reusable launch vehicle (RLV) in reentry phase is proposed based on sliding mode variable structure control technique. The aerodynamic characteristics of RLV vary rapidly, and the serious uncertainties and nonlinearities exist in the reentry flight phase. As an example, American X-34 technology demonstrator is investigated. The chattering brought by the variable structure control technique is eliminated efficiently by choosing a suitable reaching law and a sign function. A control mode of reaction control system is presented based on the RCS scheme of X-34 vehicle. As two different attitude control effectors, aerosurfaces and RCS, are employed in the reentry flight phase, a composite control strategy based on the dynamic pressure variety is presented. Also, an actuator model and a RCS thruster model are built. Analysis and nonlinear simulation results show that the sliding mode variable structure controller achieves better performance, the overshoot and steady-state error are only 0.7% and 0.04° respectively.  相似文献   

9.
Safety analysis for liquid rocket engine has a great meaning for shortening development cycle, saving development expenditure and reducing development risk. The relationship between the structure and component of liquid rocket engine is much more complex, furthermore test data are absent in development phase. Thereby, the uncertainties exist in safety analysis for liquid rocket engine. A safety analysis model integrated with FMEA(failure mode and effect analysis) based on Bayesian networks (BN) is brought forward for liquid rocket engine, which can combine qualitative analysis with quantitative decision. The method has the advantages of fusing multi-information, saving sample amount and having high veracity. An example shows that the method is efficient.  相似文献   

10.
Nozzle damping is one of the most important factors in the suppression of combustion instability in solid rocket motors. For an engineering solid rocket motor that experiences combustion instability at the end of burning, a wave attenuation method is proposed to assess the nozzle damping characteristics numerically. In this method, a periodic pressure oscillation signal which frequency equals to the first acoustic mode is superimposed on a steady flow at the head end of the chamber. When the pressure oscillation is turned off, the decay rate of the pressure can be used to determine the nozzle attenuation constant. The damping characteristics of three other nozzle geometries are numerically studied with this method under the same operating condition. The results show that the convex nozzle provides ,tre damping than the conical nozzle which in turn provides more damping than the concave nozzle. All the three nozzles have better damping effect than that of basic nozzle geometry. At last, the phase difference in the chamber is analyzed, and the numerical pressure distribution satisfies well with theoretical distribution.  相似文献   

11.
Affected by common target selection, target motion estimation and time alignment, the radar system error reg- istration algorithm is greatly limited in application. By using communication and time synchronization function of a data link network, a collaborative algorithm is proposed, which makes use of a virtual coordinates constructed by airplane to get high precision measurement source and realize effective estimation of the system error. This algorithm is based on Kalman filter and does not require high capacities in memory and calculation. Simulated results show that the algorithm has better convergence performance and estimation precision, no constrain on sampling period and accords with transfer characteristic of data link and tactical internet perfectly.  相似文献   

12.
A new guidance law, called biased retro proportional navigation (BRPN), is proposed. The guidance law is designed to intercept high-speed targets with angular constraint, which can be used for ballistic target interception. BRPN guidance law is defined, and the exact time-varying bias for a required impact angle is derived. Furthermore, the simulation results (trajectory, variation of navigation ratio, capture region, etc) are compared with those of biased proportional navigation (BPN), proportional navigation and retro-proportional navigation. The results show that, at the cost of a higher intercept time, BRPN demands lower terminal lateral acceleration and has larger capture region compared to BPN.  相似文献   

13.
1553B avionics data bus network may fail due to vibration, temperature, humidity or human error. Therefore, the research on detection technology of 1553B avionics data bus network is an important subject. The key technologies are studied by analyzing the possible faults of the network, including four-wire DC resistance measurement method for conductors-to-shield short test and stub continuity test, equivalent impedance measurement of coupling transformer for main bus continuity test, polarity reversal test base on duty ratio measurement, attenuation measurement base on coupler model, and data path integrity test base on bit error rate calculati~,,. Finally, the implementation methods of key technologies are researched, a portable integrated automatic test system of 1553B data bus network is constructed based on PC 104 computer, and the hardware configuration and test process are especially designed.  相似文献   

14.
In mathematically statistical test methods that were used to get arming distance of fuze, Langlie method has been widely applied because it only use a few samples. Monte-Carlo method was used to simulate and calculate Langlie method test of fuze arming distance by using computer. The result shows that the larger error and scatter exist in the esti- mate of arming distance variance although 50% response level of arming distance can be estimated using a little sample; the correction coefficient of variance estimate can be got by simulating and calculating, but it is useless to a certain single test; this means that a larger error exists when Langlie method test is used to get the muzzle safety distance and the arm- ing distance of fuze, and the maximum arming distance becomes shorter and the minimum one longer without correcting.  相似文献   

15.
The blockage probability and the blockage time are two important indexes for assessing the blockage efficiency of cluster munitions against the runway. The improved region-by-region searching method and the random sampling method are proposed to calculate the blockage time by considering the minimum number of craters which need to be re- paired after attack. A minimum leave window (MLW) with the minimum number of craters is found out as a region to be repaired, the blockage probability and the blockage time are calculated by the two methods in which the impact points of the sub-munitions are generated with Monte-Carlo simulation technique. An example is given to show the reasonableness of the two methods under the conditions of adequacy simulating times and enough sampling times, and how to choose the methods in application.  相似文献   

16.
A differential/integral method to estimate the kinetic parameters (apparent activation energy Ea and pre-exponential factor A) for thermal decomposition reaction of energetic materials based on Kooij formula are applied to study the nonisothermal decomposition reaction kinetics of hexanitrohexaazaisowurtzitane (HNIW) by analyzing nonisothermal DSC curve data. The apparent activation energy (Ea) obtained by the integral isoconversional non-isothermal method based on Kooij formula is used to check the constancy and validity of apparent activation energy by the differential/integral method based on Kooij formula. The most probable mechanism function of thermal decomposition reaction of HNIW is determined by a logical choice method. The equations for calculating the critical temperatures of thermal explosion (T_b) and adiabatic time-to- explosion (t_Tlad) based on Kooij formula are used to calculate the values of Tb and t_Tlad to evaluate the thermal safety and heat-resistant ability of HNIW. All the original data needed for analyzing the kinetic parameters are from nonisothermal DSC curves. The results show that the kinetic model function in differential form and the values of E_a and A of decomposition reaction of HNIW are 3(1 - α)[-ln(1 - α)]2/3, 152.73 kJ mol 1 and 10~11.97 S 1, respectively, and the values of self-accelerating decomposition temperature (T_SADT), Tb and t_Tlad are 486.55 K, 493.11 K and 52.01 s, respectively.  相似文献   

17.
The electronic structures, elastic properties and thermodynamics of MgZn2, Mg2Y and Mg2La have been determined from the first-principle calculations. The calculated heats of formation and cohesive energies show that MgzLa has the strongest alloying ability and structural stability. The structural stability mechanism is also explained through the electronic structures of these phases. The ionicity and metallicity of the phases are estimated. The elastic constants are calculated; the bulk moduli, shear moduli, Young's moduli, Poisson's ratio value and elastic anisotropy are derived; and the brittleness, plasticity and anisotropy of these phases are discussed. Gibbs free energy, Debye temperature and heat capacity are calculated and discussed.  相似文献   

18.
Through the numerical simulation investigation, the turbulent drag reduction mechanisms of shark riblet surface are explored. In allusion to the characteristics of riblets surface, the computation region, grids and flow parameters are dealt with reasonably. These present simulation results show preliminarily that 1) only the near-wall flow field above riblet surfaces is affected by riblets, and the flow within riblets is slow and quiescent; 2) the viscous sub-layer above riblet surface is thicker; 3) the shear stress and the local friction coefficient above the riblet surface are reduced, and the drag reduction quantity is larger at the bottom of riblets than that at the top. Numerical simulation investigation on the riblet surface in the paper can provide a reference for future research in this field.  相似文献   

19.
The dynamic fracture behaviors of the extraded 2024-T4 mad 7075-T6 aluminum alloys are investigated by using an instranaent ed di'op tower machine. The specimens are made fi'om a 25 irma diameter extraded circular rod. The dynamic three-point bending tests of each alloy are canied out at different impact velocities. The initiation fracture toughness mad average propagation fracture toughness of 2024-T4 mad 7075-T6 are determhaed at different loading rates. The results show that both the initiation toughness mad the propagation toughness increase with the loading rate. Fmther, the difference between the fracture toughness behaviors of 2024-T4 mad 7075-T6 is found to be dependent on the variation of fl-acVcu-e mechanism. The comprehensive fract ograpinc investigations of the fracture surfaces clearly demonstrate that the fracture mode of 2024- T4 is predominmatly transgramular fracture with high density small-sized dimples, mad the fracture mode of 7075-T6 is mainly intergramaular fracture with many intemaetalllc particles in the bottom of voids located in the fracture surface.  相似文献   

20.
The interaction and compatibility between diaminoazofuraz (DAAzF) and some energetic materials are studied by using pressure differential scanning calorimetry (DSC) method. The energetic materials include cyclotetramethylenetetranitramine (HMX), cyclotrimethylenetrinitramine (RDX), nitrocellulose (NC), nitroglycerine (NG), 125/100--NC/NG mixture (NC + NG), N-nitrodihydroxyethylaminedinitrate (DINA), aluminum powder (A1), and 3,4-dinitrofurzanfuroxan (DNTF). The results show that there are obvious interactions between DAAzF and DNTF, DINA, HMX or RDX, while weak interactions between DAAzF and NC, NG, NC + NG or A1. According to the evaluated standard of compatibility, the binary systems of DAAzF with NC, NG, NC ~ NG and A1 are compatible, the binary system of it with RDX is slightly sensitive, the binary systems of it with HMX and DINA are sensitive, and the binary system of it with DNTF is hazardous. Copyright 2013, China Ordnance Society. Production and hosting by Elsevier B.V. All rights reserved.  相似文献   

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