RU184666U1 - Unmanned aerial vehicle - Google Patents

Abstract

The unmanned aerial vehicle contains nodes for mounting on the launcher of the carrier aircraft along the fuselage, a system for stabilizing its position and controlling it in autonomous flight, a payload and an accelerating engine, in addition, it is equipped with pulse jet engines of creating a rotation pulse around a horizontal axis passing through the center of gravity unmanned aerial vehicle, and compensation for this impulse of rotation. An UAV provides an increase in the likelihood of a safe approach to a high-altitude flight path.

Description

The utility model relates to unmanned aerial vehicles (UAVs) transported by other aircraft and detached in flight for launching on a high-altitude flight path.

A UAV is known (Pegasus 11, I. Lisov, “I look at the cyclone, like a mirror ...”, the journal “Cosmonautics News”, 2017, No. 02 (409), p. 29), which is pleasant for the prototype, containing nodes for mounting on the launcher along the fuselage of the carrier aircraft, an autonomous flight control system, payload, wing, tail unit and three booster stages (booster propulsion system) with solid propellant rocket engines (solid propellant rocket engines). The launcher of the carrier aircraft contains a hydraulic UAV dump system. After separation from the launcher of the carrier aircraft, the UAV continues to fly near the carrier aircraft, with a partial loss of speed and altitude, therefore, for the safety of the carrier aircraft, after the UAV is stabilized in autonomous flight by the control system and its solid propellant rocket launch, the UAV control system provides it the flight under the fuselage of the carrier aircraft, under the influence of the propulsion of the solid-propellant rocket propulsion aircraft, the UAV flies with acceleration, overtaking the carrier aircraft, and after overtaking, the control system provides an increase in the pitch angle of the UAV and its climb flight exceeding the flight altitude of the carrier aircraft.

The essential features of the prototype, which coincide with the features of the proposed device, are as follows: an unmanned aerial vehicle containing units for mounting on the launch device of the carrier aircraft along the fuselage, a system for controlling its position in autonomous flight, a payload and an accelerating propulsion system.

The known UAV provides a high-altitude flight path in the presence of a parallel flight section of the UAV and the carrier aircraft, with a small difference in height at which the UAV overtakes the carrier aircraft and the section where the UAV maneuvers in front of the carrier aircraft by gaining flight altitude, while the distance between the carrier aircraft and the UAV, in the initial section of the set of its flight altitude, decreases. Parallel flight of a UAV and a carrier aircraft with a small difference in height and a climb to the UAV in front of the carrier aircraft increase the time the UAV is in the vicinity of the carrier aircraft, which increases the likelihood of damage to the carrier aircraft in the event of a malfunction of the UAV control system or its accelerating propulsion system.

The technical result, which the utility model is aimed at, is to reduce the likelihood of damage to the carrier aircraft in case of a malfunction of the UAV control system or its accelerating propulsion system.

To solve this problem, the proposed unmanned aerial vehicle, containing nodes for mounting on the launcher of the carrier aircraft along the fuselage, a system for controlling its position in autonomous flight, a payload and an accelerating propulsion system, is equipped with pulse jet engines of creating a rotation pulse around a transverse axis passing through the center of gravity of an unmanned aerial vehicle, with increasing pitch angle, and compensation for this rotation impulse.

Distinctive features of the proposed unmanned aerial vehicle is that the unmanned aerial vehicle is equipped with pulse jet engines to generate a rotation pulse around a transverse axis passing through the center of gravity of the unmanned aerial vehicle, with an increase in pitch angle, and compensation of this rotation pulse.

Due to the presence of these distinctive features in combination with the known, the following is achieved: the probability of damage to the carrier aircraft is reduced in case of a malfunction of the UAV control system or its accelerating propulsion system; reduction of the time of removal and fuel supply necessary for the operation of an accelerating propulsion system.

The proposed technical solution can be used in aviation, for example, to launch communication satellites or surface monitoring, research vehicles for studying space objects, cosmic radiation fluxes, and the state of the upper atmosphere.

The device is illustrated by drawings, FIG. 1 and FIG. 2.

In FIG. 1 shows a UAV device displayed on a high-altitude flight path.

In FIG. 2 shows the position of the UAV in autonomous flight relative to the carrier aircraft when the accelerating propulsion system of the UAV is turned on.

Presented in FIG. 1 and FIG. 2 UAV 1 contains attachment points to the launcher 2 of the carrier aircraft along its fuselage 3, containing a front stop 4, a lock niche 5 for lifting the UAV 1 and its mount on the launch device 2, and a rear stop 6, an accelerating propulsion system 7, a control system its autonomous flight position, including a control unit 8, in communication with the UAV stabilization device 9 after separation from the launch device 2, and with the UAV 1 position control device 10 after starting the booster engine 7. UAV 1 is equipped with a payload 11, a pulse jet engine 12, to create a pulse of rotation around the transverse axis passing through the center of gravity 13 of the UAV 1, and a pulse jet engine 14, to create a pulse to compensate for the rotation of the UAV 1 around the transverse axis passing through the center of gravity 13 . The launch device 2 contains sliding elements 15 for lifting the UAV 1 and its mounting on the launch device 2 and is configured to separate the UAV 1 from the carrier aircraft in flight.

Presented in FIG. 1 and FIG. 2 UAV 1 operates as follows. By lifting means of the launching device 2 (not shown in the drawings), the UAV 1 is installed on the starting device 2 until it contacts the front and rear stops 4 and 6, the sliding elements 15 are fixed in the locking recess 5. The carrier aircraft flies to the hitch with a rise to a height uncoupling. In the place of uncoupling, the sliding elements 15 and the UAV 1 are released under the action of gravity and are separated from the starting device 2. If necessary, the starting device 2 may include a repulsion device for the UAV 1 (not shown in the drawings). After separation of the UAV 1, at the command of the control unit 8, the device 9 is activated, providing stabilization of the position of the UAV 1 in autonomous flight, in which the pulse jet engine 12 is located in the lower part of the UAV 1, and the pulse jet engine 14, respectively, in the upper one. In this position, the UAV 1 control unit 8 activates a pulsed jet engine 12, providing a pulse of rotation of the UAV 1 around the transverse axis passing through the CT 13. In this case, the UAV 1 rotates counterclockwise, increasing the pitch angle (inclination to the horizontal plane). In the process of increasing the pitch angle to the required value ϑ (Fig. 2), according to the signals of the control unit 8, a pulse jet engine 14 for compensating the rotation momentum about an axis passing through the central heating center 13 is activated. The turn-on time of the jet engine 14 is determined by calculation and during the development of the UAV 1 specify tests, from the condition of reducing the angular velocity of rotation of the UAV 1 to a value of ~ 0 angular degrees per second, when UAV 1 reaches the required value ϑ pitch angle. At this point in time, the acceleration propulsion system 7 is started according to the signal of the control unit 8. The process of increasing the pitch angle of the UAV 1 to the required value ϑ takes place in ~ 1 s, and leads to an additional decrease in the horizontal component W 'of the _{UAV of the} speed of the UAV 1 to ~ 80- 120 m / s and an increase in the distance between UAV 1 and fuselage 3 to ~ 400 m, at a speed of the carrier aircraft ~ 270 m / s. With a further increase in the flight height of the UAV 1 at an angle ϑ of pitch, the distance between the UAV 1 and the fuselage 3 of the carrier aircraft will increase. Thus, the minimum time (~ 2 s) of UAV flight 1 at a distance of 0-60 m from the fuselage 3 of the carrier aircraft is provided, in contrast to the prototype, where this time is longer for the flight time under the fuselage 3 of the carrier aircraft. The short time spent by UAV 1 near the fuselage 3 of the carrier aircraft reduces the likelihood of damage to the carrier aircraft when the control system of the UAV 1 or the accelerating propulsion system 7 fails. Additionally, unlike the prototype, there is no parallel flight section of the UAV 1 under the fuselage 3 of the carrier aircraft, bringing to a high-altitude flight path, provides a reduction in the time of removal and fuel supply necessary for the operation of an accelerating propulsion system 7.

Claims (1)

An unmanned aerial vehicle containing units for mounting on the launcher of the carrier aircraft along the fuselage, a system for controlling its position in autonomous flight, a payload and an accelerating propulsion system, characterized in that it is equipped with pulse jet engines to create a rotation pulse around the transverse axis passing through the center the severity of the unmanned aerial vehicle, with an increase in the pitch angle, and compensation for this rotation impulse.

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