RU2618811C1 - Method for determining conditions of possible unmanned aircraft launch - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: for determining the launch possibilities target coordinates, number and position of rout change points, gunnery course, approach to the target angle, target designation angle, target characteristic and size, fuel type, wind speed are entered using the first user interface, current parameters of the carrier are displayed, expected target search root point, unmanned aircraft (UMAC) time of reaching the attack line, probability of target capture by active radar-homing head, minimum and maximum range of the UMAC use, method of detecting target, the total UMAC flight path to the target, required amount of fuel are calculated at regular intervals in the calculating module and displayed on the screen of the second carrier user interface, UMAC flight path diagram, the tatget, rout change points,UMAC flight path, target position ambiguity area, target search root point, attack line radius, antenna roll angle are displayed on the screen using the third user interface, flight mission is transmitted to the UMAC and start enabling signal is made if parameters enter specified limiting range.

EFFECT: accuracy of determining the UMAC launch command moment from different types of carriers.

3 dwg

Description

The proposed technical solution relates to the field of information and measurement technology and can be used in the computing module of the carriers of unmanned aerial vehicles (UAVs).

The prior art method for determining the separation point of the rocket stages, based on the movement along the programmed path of the separating stage in the launch plane, which determines the closest and located at the optimal distance from the launch point permitted areas of incidence of the separating stage of the rocket, compare the predicted coordinates of the point of incidence of the separating stage with the coordinates of the permitted fall zone, estimate the amount of fuel remaining in the tanks of the rocket’s separating stage and give the command to separate the stage. [one]

This method is difficult to use in UAVs due to the large size of the computing module of the rocket.

The prior art method of determining the moment of issuing a command to launch an ammunition, in which the ammunition is launched and the ammunition is directed along the programmed path, the ammunition speed is calculated, the distance to the target is calculated, the coordinates of the meeting point with the target are calculated, the length of time between the start and detonation of the ammunition is selected and undermine the ammunition. [2]

The disadvantage of this method is the lack of accuracy in determining the moment of issuing a command to launch an ammunition.

Closest to the technical solution under consideration and adopted as a prototype is a method for determining the moment of issuing a command to launch a rocket from an aircraft carrier, which uses algorithms for the combat use of an arms control system.

Algorithms for ensuring the use of weapons include: calculating the conditions for permitting launching a rocket, forming a launch logic, calculating flight tasks and commands, forming an indication of the conditions of use. Special software is introduced into the on-board digital computer, which is part of the on-board automated control system, containing the main control program, mode controllers, functional software, and built-in control programs. [3]

The disadvantage of this method is the impossibility of its use for different types of media.

The objective of the invention is to eliminate the above disadvantages and create a method for determining the conditions for the possible launch of an UAV, which allows you to accurately determine the time of issuing a command to start an UAV from different types of carriers.

The problem is solved due to the fact that determining the conditions for a possible UAV launch is carried out as follows: using the first user interface of the carrier enter the coordinates of the target position, the number and coordinates of the points of route change, the firing rate, the angle of approach to the target, target designation angle, sign and target size , type of fuel, wind speed, and also display the current parameters of the carrier, while at equal intervals in the computing module of the carrier, the point of the expected start of the search is calculated and, the UAV’s exit time to the attack line, the probability of target acquisition by an active homing radar, the minimum and maximum UAV range, the target detection method, the total UAV flight path to the target and the amount of fuel needed for this, the data obtained is displayed using the screen of the second user interface carrier, using the third user interface on the screen displays a chart displaying the path of the UAV flight mission: UAV launch point, target, route change points the UAV flight path, the target position uncertainty zone, the target search start point, the radius of the attack line, the antenna’s pumping angle, and if the probability of target capture, the amount of fuel in the UAV, flight mission parameters, and current carrier parameters are within specified ranges, the flight mission is transmitted to the UAV and permission is given to launch it.

The proposed method can be used when placing UAVs on various types of carriers.

In the case of placing an UAV on an aircraft carrier, using the first user interface, they additionally enter: the temperature of the outside air near the ground before take-off of the carrier, and also display the current parameters of the carrier: coordinates of the carrier’s position, heading angles, roll, pitch, speed and altitude.

In the case of placing an UAV on a ship’s carrier, the current user’s parameters are displayed on the screen of the first user interface: coordinates of the carrier’s position, movement speed and course angles, roll and pitch.

In the case of placing a UAV on a car carrier, the coordinates of the carrier position are displayed on the screen of the first user interface.

An estimate of the amount of fuel residues in the rocket tanks is called the solution to the problem of reaching the target.

The invention is illustrated by figures, which represent:

FIG. 1 is a screen view of a first user interface;

FIG. 2 is a screen view of a second user interface;

FIG. 3 is a screen view of a third user interface.

In FIG. 1, 2, 3 are indicated:

1 - coordinates of the target position;

2 - the number and coordinates of route change points;

3 - course of fire;

4 - angle of approach to the goal;

5 - target designation angle;

6 - sign and target size;

7 - type of fuel;

8 - wind speed;

9 - current coordinates of the position of the medium;

10 - current speed and height of the carrier;

11 - current angles of the course, roll and pitch of the carrier;

12 is a method of detecting a target;

13 - the probability of target capture ARGSN;

14 - UAV exit time to the line of attack;

15 - the total range of UAV flight to the target;

16 - the amount of fuel necessary for approaching the target;

17 - minimum and maximum range of UAV application;

18 - UAV flight path;

19 - starting point;

20 - points change route;

21 is the goal;

22 - zone of uncertainty of the position of the target;

23 - start point of the target search;

24 - radius of the line of attack;

25 - angle pump antenna.

A method for determining the conditions for a possible UAV launch, in which using the first user interface of the carrier enter the coordinates of the target 1 position, the number and coordinates of route change points 2, the firing rate 3, the angle of approach to the target 4, target angle 5, sign and target size 6, type fuel 7, wind speed 8, and also display the current parameters of the carrier 10, 11. At equal intervals in the computing module of the carrier, calculate the point of the expected start of the search for target 19, the UAV exit time at attack line 14, the probability of target acquisition by an active homing radar 13, minimum and maximum range of UAV application 17, target detection method 12, total UAV flight range to target 15 and the required amount of fuel 16. The results are displayed on the screen of the second media user interface using the screen the third user interface displays a chart displaying the flight path (flight task) of the UAV 18: the zone of uncertainty of the position of the target 22, the start point of the search for the target 23 and the radius ru attack attack 24, target position 21, position of route switching points 20, antenna pumping angle 25. If the probability of target capture 13, the amount of fuel in the UAV 16, flight mission parameters, as well as current carrier parameters 10.11 are within the specified ranges, in the UAV transmit the flight mission and give permission to launch it.

When implementing the method, a UAV simulator is placed on a test bench and software is debugged using control tasks.

When implementing the method, the option of placing a UAV on an aircraft carrier can be used, in this case, using the first user interface, the outside temperature of the earth is additionally entered before take-off of the carrier, and also the current parameters of the carrier are displayed: coordinates of the position of the carrier, heading angles, roll, pitch, flight speed and altitude.

When implementing the method, the option of placing an UAV on a ship’s carrier can be used, while on the screen of the first user interface of the carrier its current parameters are displayed: coordinates of the carrier’s position, speed and angles of course, roll and pitch.

When implementing the method, the option of placing a UAV on an automobile carrier can be used, while the coordinates of the carrier position are displayed on the screen of the first user interface.

The coordinates of route change points and the calculation of the UAV trajectory parameters can change during carrier movement, taking into account the terrain, as well as the least chance of missile loss from the antagonist forces of the alleged enemy.

Prior to launching the UAV, according to intelligence provided by the navigation equipment of the carrier, the sign and size of the target, as well as the number of assigned missiles in a salvo, can be adjusted.

Let us consider the formation of permitted shooting conditions and target selection logic when placing an UAV on an aircraft carrier, at the same time: choose a target, select route change points, choose parameter limits allowing UAV use (current carrier height, heading angles, roll, carrier pitch and instrumental flight speed of the carrier ), develop an algorithm for calculating the UAV motion in the horizontal plane, calculate the parameters of the UAV motion path in the horizontal plane in the coordinate system associated with the carrier, I calculate the parameters of the UAV trajectory in the vertical plane, iteratively calculate the total UAV flight path, develop algorithms for calculating the radius of the attack line, the uncertainty of the target position, and the circle to limit the setting of route change points. Before the start of the first iteration, the input parameters are zeroed, the output parameters of the current iteration become input for the next, the exit from the iterations occurs if the difference between the results of the previous and subsequent iteration does not exceed the specified value or the number of iterations has exceeded 10. The method of shooting is determined, and the possible maximum and minimum ranges are calculated to the goal, solve the problem of reaching the target, calculate the time to reach the line of attack, form the logic of target selection, form a binding to the coordinate system, zanny with the carrier.

The method can be implemented using installed on the carrier: navigation equipment, sighting and navigation system and computing module.

Navigation equipment includes: inertial control system, Doppler speed component meter and satellite navigation system.

As an aiming and navigation complex, a laser-aiming system can be used, which is used in the Kaira weapon systems.

The computing module of the carrier contains an arms control system and a weapon control system. The weapons control system includes: an on-board automated control system containing special software consisting of the main control program, mode controllers, functional software, built-in control program, as well as information display algorithms on user interface screens. The weapon control system contains special software, in particular, the software for preparing the launch vehicle for launching an unmanned aerial vehicle.

The proposed method for determining the conditions for a possible UAV launch allows you to accurately determine the moment of issuing a command to launch an UAV from different types of carriers.

The presented figures and the description of the method allow, using the existing elemental base, to implement it, which characterizes the proposed method as industrially applicable.

Submitted analogues

1. RU, application No. 2013157666, priority date 12/24/2013, IPC B64G 1/40;

2. RU, patent No. 2525303, priority date 10/05/2011, IPC F41F 3/00, G01S 7/38;

3. Fighter Weapons Control Systems: The Foundations of the Intelligence of a Multifunctional Aircraft / Edited by Academician E.A. Fedosova. M.: Mechanical Engineering, 2005, pp. 31-37.

Claims (1)

A method for determining the conditions for a possible launch of an unmanned aerial vehicle, in which using the first user interface of the carrier enter the coordinates of the target position, the number and coordinates of points of route change, the firing rate, the angle of approach to the target, target angle, sign and size of the target, fuel type, wind speed , and also display the current media settings, at the same time intervals in the computing module of the media calculate the point of the expected start of the target search, the exit time of unmanned the aircraft at the attack line, the probability of the target being captured by an active homing radar, the minimum and maximum range of an unmanned aerial vehicle, the method of detecting a target, the total flight path of an unmanned aerial vehicle to the target and the amount of fuel needed for this, the data are displayed using the second screen the user interface of the medium, using the third user interface on the screen display a diagram showing the trajectory n flight mission of an unmanned aerial vehicle: launch point of an unmanned aerial vehicle, target, route change points, unmanned aerial vehicle flight path, target position uncertainty zone, target search start point, radius of attack line, antenna pumping angle, while if the probability of target capture, the amount of fuel in the unmanned aerial vehicle, the parameters of the flight task, as well as the current parameters of the carrier are within the specified ranges, the unmanned aerial vehicle is transmitted t flight task and gives permission to start.

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