RU167155U1 - THREE-PHASE RING HELL FOR ACCELERATION OF LA - Google Patents

Abstract

A device for accelerating an aircraft, containing an axis, a shaft, a trough, a frame, an S-shaped screw, a counterweight, jet engines, an asymmetric bearing, gyroscopes, a wheel rim, is additionally equipped with a stator with 3N coils of three-phase BP along the rim conjugated with the axis, a rotor with 3N three-phase AD coils coupled to the rim, stator coils with four-wire lines through a 50N Hz self-oscillating generator are coupled to a battery coupled through a bridge rectifier circuit and a circuit breaker with a three-phase voltage line of 380 V, while AC The metric bearing is coupled to the axis through a damping system.

Description

The utility model relates to aviation and astronautics.

Known asynchronous motors (HELL) 3-phase / S.G. Kalashnikov. Electricity. M .: "Science", 1977, 592 pp. /. Their disadvantage is the limited amount of torque.

Known launchers of aircraft (LA) (Patent No. 0157840 RU 2015)

Their disadvantage is the use of heavy flywheels and several stages of the accelerator.

The task of the utility model in creating an aircraft with the possibility of multiple instantaneous huge accelerations without using heavy flywheels due to the ring 3-phase high-frequency (HF) blood pressure and damping of the conjugation of the aircraft and high-frequency blood pressure during accelerations.

The problem is solved in that the device containing the axis, shaft, wheel, trough, frame, s-shaped screw, jet engine aircraft, counterweight, 2nd and 3rd jet engines, asymmetric bearing, arrestor, gyroscopes, wheel rim, additionally equipped with a stator with 3N coils of 3-phase BP along the rim conjugated with the axis, a rotor with 3N coils of 3-phase BP coupled with the rim, stator coils with 4-wire lines through a 50N Hz self-oscillating frequency generator. coupled to a battery coupled through a bridge rectifier circuit and a switch with a 3-phase voltage line of 380 V; Aircraft with an asymmetric bearing through a damping system are mated to an axis.

In FIG. 1 shows a diagram of the device, where 1 is the axis, 2 is the shaft, 3 is the wheel, 4 is the trough, 5 is the frame, 6 is the s-shaped screw, 7 is the aircraft with 8 is the jet engine, 9, 10 is the 2nd and 3 jet engines, 11 - an asymmetric bearing, 12 - an arrestor, 13 - gyroscopes, 14 - a wheel rim, 15 - a stator with 3N coils of 3-phase BP, 16 - a rotor with 3N coils of 3-phase BP, 17 - 4-wire lines, 18 - 50N Hz self-oscillating frequency generator., 19 - battery, 20 - bridge rectifier circuit, 21 - circuit breaker, 22 - 3-phase voltage line 380 V, 23 - damping system, 24 - counterbalance. The dotted and dash-dotted lines show the locations of the coils of the stator and rotor, respectively. Arrows - the direction of movement of the elements of the device during the acceleration of the aircraft.

On axis 1, shaft 2 can rotate with wheel 3, where the groove 4 is located, directing when accelerating the asymmetric bearing 11 with LA 7 in accordance with the equations

where R, R ′ _t is the distance of the aircraft from the axis of rotation at the current time t and the derivative of this distance with respect to time; w, dV _t , dV _n - respectively, the angular velocity, increments of the tangential and normal speeds of the aircraft at the current time t to compensate for the Coriolis force, i.e. reaction forces to the tangential component of centrifugal force.

Frame 5 with an s-shaped screw 6 serves to maintain a zero value of its torque in the plane of angular acceleration of aircraft 7 in dense layers of the atmosphere. In sparse layers, the function of the screw 6 is performed by the 3rd jet engine 10.

A jet engine 8 is needed to overcome air resistance in the first moments of the separation of the aircraft 7 from the groove 4 in the dense layers of the atmosphere.

The 2nd jet engine 9 provides a lift of the device in dense and rarefied layers of the atmosphere before launching the LA 7 to reduce the magnitude of the shock wave while overcoming the sound barrier.

The asymmetric bearing 11 and the arrestor 12 prevent the rotation of the aircraft 7 before starting.

Gyroscopes 13 together with 11 serve for the necessary rotation of the centrifugal force in hundredths of a second at the moment of launching the LA 7. Gyroscopes 13 also eliminate the rotation of the LA 7 when the damping system 23 is triggered in the first moments after the LA 7 is separated from the trench 4.

The rim of the wheel 14 transmits rotation to the groove 4 and is rigidly coupled to the rotor 16, which provides a large torque of electromagnetic forces together with the stator 15 at the time of acceleration of the aircraft 7.

4-wire lines 17 transmit in the required phase an electric current to 3N coils placed evenly along the perimeter of the rim 14.

A self-oscillating generator 18 with an operating frequency of 50N Hz maintains approximately the rotational speed of the rotor 16 with an N-fold torque equal to the order of slightly less than 50 Hz, taking into account slippage.

The battery 19 is charged through a rectifier circuit 20 from a 3-phase voltage line 22 and during an autonomous flight of the device during the launch of the aircraft 7 after the operation of the switch 21 ensures the operation of the HF HELL.

The battery 19 is charged through a rectifier circuit 20 from a 3-phase voltage line 22 and during an autonomous flight of the device during the launch of the aircraft 7 after the operation of the switch 21 ensures the operation of the HF HELL.

The damping system 23 after separation of the aircraft 7 performs docking 7 with the remaining elements of the device subject to the conditions:

where M, V, m, V ₁ - respectively, the mass of the aircraft 7, the speed of the aircraft 7 after separation from the trough 4, the mass of the elements of the device without the mass of the aircraft 7, the speed of the device after docking with the aircraft 7;

where dV is the change in the speed of the aircraft 7 after docking; m << M.

Obviously, the extent and elasticity of the system 23 should ensure the fulfillment of the inequality:

where dt is the duration of the docking, 10g is the maximum allowable pilot overload during a jerk during the docking.

Note that the speed of LA 7 after undocking at w = 50 Hz and a wheel radius of 3 15 m is approximately 3 km / s higher than the linear speed of the rotor 16, and the rotor speed is 2пRw = 6 15 50 = 4500 m / s higher than the speed of the stator 15 and therefore, the damping system 23 consists of two parts, each representing telescopic rings coupled by a flexible coupling.

The counterweight 24 when starting the LA 7 provides its offset the location of the center of mass of the entire device on the axis of rotation and detaches from the device simultaneously with the separation of the LA 7.

Instead of system 23, a “jamming” can occur, stopping the LA 7 at the edge of the gutter 4 after an earlier separation of the counterweight 24 compared to the separation of the LA 7. In this case, the LA 7 is in the center of mass, because m << M, and the resulting rotation is eliminated by the operation of the taxiway 10.

The device operates as follows.

In the initial state, the aircraft 7 is covered, the high-frequency blood pressure is off, 21 are open. Turning on 21 charges the battery 19 and turning on the HF motor increases the angular speed of rotation of the wheel 3. When you turn on the 2nd and 3rd jet engines (RD), the device rises to the required height of about 10 km. Upon reaching a rotation speed of 3 of the order of 50 Hz. RD 8 is turned on, gyroscopes 13 are removed, the arretation 12 and LA 7 with an asymmetric bearing 11 are removed, while accelerating along the groove 4, they are undocked synchronously with the counterweight 24 from the wheel, frame, and high-frequency blood pressure. The damping system 23 is triggered, the high-frequency blood pressure is turned off, the aircraft 7 approaches and joins the remaining elements of the device (but without counterweight 24), continuing the flight by inertia or using the taxiway 8.

Thus, the aircraft has the possibility of multiple instantaneous huge accelerations without the use of heavy flywheels.

Claims (1)

A device for accelerating an aircraft, containing an axis, a shaft, a trough, a frame, an S-shaped screw, a counterweight, jet engines, an asymmetric bearing, gyroscopes, a wheel rim, is additionally equipped with a stator with 3N coils of three-phase BP along the rim conjugated with the axis, a rotor with 3N three-phase AD coils coupled to the rim, stator coils with four-wire lines through a 50N Hz self-oscillating generator are coupled to a battery coupled through a bridge rectifier circuit and a circuit breaker with a three-phase voltage line of 380 V, while AC The metric bearing is coupled to the axis through a damping system.

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