RU2727770C1 - Unmanned aerial vehicle - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: invention relates to aircraft engineering, particularly, to systems for launching of unmanned aerial vehicles from aircraft carriers. Unmanned aerial vehicle comprises units for fixation on launching device of carrier aircraft, acceleration propulsion system, control system of its position in autonomous flight, payload, as well as pulse jet engines for creation of rotation pulse around transverse axis passing through gravity center of unmanned aerial vehicle, with pitch angle increase, and compensation of this rotation pulse. UAV is equipped with braking parachute, which comprises canopy, rope and slings connecting canopy with rope. UAV is equipped with a box fixed on the UAV from the tail part through the box fixing device, configured to unfix its attachment, and a device for fixing the end section of the cable in the zone of the upper point of the surface of the tail part, configured to unfix the attachment. Canopy, slings and initial section of rope are packed in box, and final section of parachute rope is fixed in its attachment device.

EFFECT: reduced weight of unmanned aerial vehicle and time of its launching to altitude flight path.

1 cl, 6 dwg

Description

The invention relates to unmanned aerial vehicles (UAVs), transported by other aircraft and detachable in flight for launching to a high-altitude flight path.

Known UAV, patent RU No. 2702261, taken as a prototype, containing assemblies for attachment to the launching device of the carrier aircraft along the fuselage, made with the possibility of separating it in flight, a booster propulsion system, a control system for its position in autonomous flight, a payload, and pulse jet engines, creating a rotation impulse around a transverse axis passing through the center of gravity of the unmanned aerial vehicle, with an increase in the pitch angle, and compensating for this rotation impulse.

All essential features of the prototype coincide with the essential features of the proposed device.

The known UAV is made with the shape of the outer surface, which provides the minimum aerodynamic resistance in the flow of atmospheric air around it, to reduce the fuel mass of the booster propulsion system required for flight and the mass of the UAV as a whole. The minimum aerodynamic drag of the UAV after its separation provides a decrease in the acceleration of UAV deceleration in the stream of air flowing around, as a result of which the time for removing the UAV from the carrier aircraft to a safe distance and the loss of flight altitude before the launch of the accelerating propulsion system increase. To compensate for the loss of UAV flight altitude, the fuel of the booster propulsion system is consumed, which increases the required fuel mass of the booster propulsion system.

The technical result to be achieved by the technical solution is to reduce the required fuel mass of the booster propulsion system.

To solve this problem, an unmanned aerial vehicle containing nodes for attachment to the launch device of the carrier aircraft along the fuselage, made with the possibility of separating it in flight, a booster propulsion system, a system for controlling its position in autonomous flight, a payload, and pulse jet engines, creating an impulse of rotation around the transverse axis passing through the center of gravity of the unmanned aerial vehicle, with an increase in the pitch angle, and compensating for this impulse of rotation, is equipped with a braking parachute containing a canopy, a cable and slings connecting the canopy with a cable, and is also equipped with a box attached to the unmanned aerial vehicle aircraft from the tail side through the box fastening device, made with the possibility of unlocking its fastening, and the device for fastening the end section of the cable in the area of the upper point of the tail part surface, made with the possibility of unlocking the fastening, while the canopy, slings and the initial part of the cable is packed in a box, and the end section of the cable is fixed in the device for its fastening.

Distinctive features of the proposed unmanned aerial vehicle is that the unmanned aerial vehicle is equipped with a braking parachute containing a canopy, a cable and slings connecting the canopy with a cable, and is also equipped with a box attached to the unmanned aerial vehicle from the tail end through a box fastening device made with the possibility of unlocking its fastening, and a device for fastening the end section of the cable in the area of the upper point of the surface of the tail part, made with the possibility of unlocking the fastening, while the dome, slings and the initial section of the cable are packed in a box, and the end section of the cable is fixed in the device for its fastening.

Due to the presence of these distinctive features in combination with the known ones, a decrease in the time the UAV reaches the high-altitude flight trajectory and the fuel supply required for the operation of the booster propulsion system, as well as a decrease in the mass of the UAV as a whole, before the launch of the acceleration propulsion system is achieved.

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

The device and its operation are illustrated by drawings, FIG. 1 to FIG. 6.

FIG. 1 shows the UAV device, displayed on the high-altitude flight trajectory.

FIG. 2 shows the position of the UAV in autonomous flight after separation from the carrier aircraft when its position is stabilized during braking by a stream of air and unlocking the box fastening device.

FIG. 3 shows the position of the UAV in autonomous flight after moving away from the carrier aircraft to a safe distance for launching to the high-altitude flight path before unlocking the attachment of the end section of the parachute cable and turning on the jet engine to create a rotation impulse around the transverse axis passing through the center of gravity of the unmanned aerial vehicle.

FIG. 4 shows a view of FIG. 2 in the direction of arrow A in case of accidental deviation or oscillations of the UAV along the course at an angle β, explaining the formation of a stabilizing moment M _β from the tension force of the parachute cable, the opposite direction, returning the UAV to its original state.

FIG. 5 shows views of FIG. 2 in the direction of arrow A in case of random deviation or oscillations of the UAV along the roll at an angle γ (rotation around the longitudinal axis of the UAV) explaining the formation of the stabilizing moment M _γ from the pulling force of the parachute cable in the opposite direction, returning the UAV to its original state.

FIG. 6 shows the position of the UAV in autonomous flight relative to the carrier aircraft when the UAV's booster propulsion system is launched.

Shown in FIG. 1-6 UAV 1 contains attachment points on the launch device 2 of the aircraft carrier along its fuselage 3, consisting of a front stop 4, a lock niche 5 for lifting the UAV 1 and fixing it on the launch device 2, and a rear stop 6, an accelerating propulsion system 7 , a control system for its position in autonomous flight, including a control unit 8 communicated with the device 9 for stabilizing the position of the UAV 1 after separation from the launching device 2, and with the device 10 for controlling the position of the UAV 1 after the launch of the accelerating propulsion system 7. The 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 (CG) of the UAV 1, with an increase in the pitch angle, 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 13 gravity. The launching device 2 contains sliding elements 15 for lifting the UAV 1 and fixing it on the launching device 2 and is configured to separate the UAV 1 from the aircraft carrier in flight. UAV 1 is equipped with a braking parachute containing a canopy 16, slings 17 and a cable 18. Slings 17 connect the canopy 16 with a cable 18. UAV 1 is equipped with a box 19, secured from the tail of the UAV 1 through a device 20 for fastening the box 19, made with the possibility of unlocking it fastening, and a device 21 for fastening the end section of the cable 18 in the area of the upper point of the surface of the tail part of the UAV 1, made with the possibility of unlocking its attachment, while the dome 16, slings 17 and the initial section of the cable 18 are packed in a box 19, and the end section of the cable 18 is fixed in the device 21 of its fastening.

UAV 1 works as follows. By means of lifting the launcher 2 (not shown in the drawings), the UAV 1 is installed on the launcher 2 until contact with the front and rear stops 4 and 6, the sliding elements 15 are fixed in the lock niche 5. The carrier aircraft flies to the place of detachment with a rise to a height uncoupling. In the place of uncoupling, sliding elements 15 are unlocked and the UAV 1 is separated from the launcher 2 by gravity. If necessary, the launcher 2 may contain a repulsion device for the UAV 1 (not shown in the drawings). After the separation of the UAV 1, at the command of the control unit 8, device 9 is activated, providing stabilization of the position of the UAV 1 in autonomous flight, in which the impulse jet engine 12 is located in the lower part of the UAV 1, and the impulse jet engine 14, respectively, in the upper part. When the position of the UAV 1 is stabilized, the device 20 for fixing the box 19 is unlocked, which leads to the separation of the box 19 from the UAV 1. The dome 16, its lines 17 and the initial section of the cable 18 are in the air flow around the UAV 1. The dome 16 opens (see Fig. 2), perceiving the dynamic pressure of the air flowing around. The force F _P from the dynamic pressure of the air flow to the dome 16 through the lines 17 and the cable 18 is transmitted to the zone of the upper point of the surface of the tail of the UAV 1. Force F _{P is} directed in the opposite direction from the direction of flight of the UAV 1 and creates additional, in relation to the braking of the UAV 1 air flow around, negative acceleration acting on the UAV 1 and further reducing its flight speed, in relation to the speed of the carrier aircraft. In addition, the force F _P, due to the action in the zone of the upper point of the surface of the tail of the UAV 1, creates a moment M _{ϑ of} rotation of the UAV 1 relative to its center of gravity 13, increasing the pitch angle ϑ: M _ϑ = F _P * h _ϑ , where h _ϑ is the shoulder of the force F _P relative to the center of gravity of the UAV 1 (see Fig. 2), therefore, by the time the required distance (L _beats ) is reached, the distance of the UAV 1 from the carrier aircraft, which ensures the safety of the carrier aircraft when the UAV 1 is brought to a high-altitude flight path, at launch pulse jet engine 12, UAV 1 is located at a preliminary pitch angle ϑ _P (see Fig. 3), therefore, to achieve the value of the angle ϑ _ZAP pitch of the UAV 1 required to start the accelerating propulsion system 7, the pulse jet engine 12, compared with the prototype , provides an increase in the pitch angle of the UAV 1 by a smaller value (ϑ _ZAP -ϑп), which provides a decrease in fuel consumption for increasing the pitch angle, respectively, the fuel consumption of the impulse jet engine 14 creating a pulse to compensate for the rotation of the UAV 1. Due to the additional decrease in the flight speed of the UAV 1, in relation to the speed of the carrier aircraft, the time required to reach the required distance (L _beats ) of the UAV 1 removal from the carrier aircraft is reduced, ensuring the safety of the carrier aircraft during launching UAV 1 on the high-altitude flight path. Due to a decrease in the time to reach the required distance (L _beats , see Fig. 3) of the UAV 1 removal from the carrier aircraft, the loss of altitude (AH) of the UAV 1 flight also decreases, relative to the flight altitude of the carrier aircraft, when the pulsed jet engine 12 is turned on and , respectively, when starting the booster propulsion system 7, which provides a decrease in the time of launching the UAV 1 to the high-altitude flight trajectory, and the necessary fuel supply for the acceleration propulsion system 7, a decrease in its mass and the mass of the UAV 1 as a whole. Reducing the mass of the UAV 1 ensures its greater acceleration under the action of the traction force of the accelerating propulsion system 7, which further reduces the time taken to bring the UAV 1 to the high-altitude flight path. In addition, under the action of the force F _P and random rotation or oscillations of the UAV 1 along the course at an angle β (see Fig. 4), the force F _P , relative to the center of gravity 13, acts on the shoulder h _β , creating a moment of rotation M _β = F _П * h _β , of the opposite direction, which returns the UAV 1 to its original state, providing stabilization of the UAV 1 along the course. Similarly, the torque of rotation of the opposite action is also formed when the UAV 1 turns along the course in the opposite direction (by an angle of minus β). Under the action of the force F _P and random rotation or oscillations of the UAV 1 along the roll around its longitudinal axis at an angle γ (see Fig. 5), the point of application of the force F _P is displaced relative to the vertical plane, while the cable 18 is located at an angle to it and the force F _{P is} decomposed into a longitudinal component (F _P-PR ) and a lateral component (F _P-B ). The lateral component F _P-B , relative to the center of gravity 13, acts on the shoulder h _γ , creating a moment of rotation M _γ = F _P-B * h _γ , opposite action, which returns the UAV 1 to its original state, ensuring the stabilization of the UAV 1 on the roll. Similarly, the torque of opposite action is also formed when the UAV 1 rolls in the opposite direction (by an angle of minus γ). Due to the stabilization of the UAV 1 along the course and the roll, the fuel reserve required for the operation of the device 9 for stabilizing the position of the UAV 1 from the moment of its separation from the launcher 2 until the required distance L _{beats is} reached. After reaching the required distance L _{beats of the} UAV 1 distance from the carrier aircraft, the control unit 8 activates the release of the device 21 for securing the end section of the cable 18 and the impulse jet engine 12, which increases the UAV 1 pitch angle. In the process, the UAV 1 pitch angle increases to the required value ϑ _ZAP (Fig. 6), according to the signals of the control unit 8, a pulsed jet engine 14 is activated, providing compensation for the impulse of rotation of the UAV 1 around the transverse axis passing through the CG 13, and after reducing the angular speed of rotation of the UAV 1, the accelerating propulsion system 7 is launched.

Claims (1)

An unmanned aerial vehicle containing assemblies for attachment to the launch device of the carrier aircraft along the fuselage, made with the possibility of its separation in flight, an accelerating propulsion system, a system for controlling its position in autonomous flight, a payload, as well as pulse jet engines to create a pulse of rotation around the transverse axis passing through the center of gravity of the unmanned aerial vehicle, with an increase in the pitch angle, and compensation for this impulse of rotation, characterized in that it is equipped with a braking parachute containing a canopy, a cable and slings connecting the canopy with a cable, and is also equipped with a box attached to the unmanned aerial vehicle aircraft from the tail side through the box fastening device, made with the possibility of unlocking its fastening, and the device for fastening the end section of the cable in the area of the upper point of the tail part surface, made with the possibility of unlocking the fastening, while the dome, slings and the initial section the cables are packed in a box, and the end section of the cable is fixed in the device for its fastening.

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