A METHODICAL APPROACH TO INCREASE THE ACCURACY OF THE USE OF UNGUIDED AIRCRAFT MISSILES BY TAKING INTO ACCOUNT THE TEMPERATURE OF SOLID FUEL ENGINES
DOI:
https://doi.org/10.54858/dndia.2022-18-22Keywords:
ballistite, unguided aircraft missiles, full reduction, full traction impulse, solid propellant missiles engineAbstract
In the process of in-depth research into the technical condition of the unguided aircraft missiles (UAM), the dependence of the full thrust impulse () of their rocket engines on the temperature of the external environment was revealed, which in the working temperature range (from 15°С to -50°С) can vary within 8 ... 10 % depending on type of fuel. The article presents the results of research on the possibility of increasing the accuracy of the solution of the aiming task by UAM by taking into account the influence of the temperature of the charge of a solid fuel rocket engine on the total thrust impulse and, as a result, on the accuracy of the solution of the aiming task.
The basis of the decision of this task was the method of conducting engineering and navigational calculations of ballistic support for UAM firing and a number of provisions of the theory of solving the task of aiming at ground targets from aircraft, taking into account generally accepted assumptions, the main ones of which are: the speed of the missile at the end of the active section is determined only by the thrust of the engine and resistance; the law of resistance along the entire trajectory is assumed to be constant; on the passive part of the trajectory, the UAM moves like an ordinary artillery projectile, while the UAM is considered as a projectile with a complex ballistic pattern of movement, consisting of active and passive sections.
Taking into account the influence of the temperature of the engine charge on the ballistic characteristics of the UAM in the form of some aiming correction will improve the accuracy of application within the effective launch range.
In the future, taking into account the aiming correction according to the temperature of the rocket fuel must be carried out during the development of mathematical support (algorithms) for the aiming systems of prospective military aircraft.
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