Impactor apparatus operated from rotorcraft
An impactor apparatus for use with a rotorcraft, comprises a reeling apparatus adapted to be transported by the rotorcraft, the reeling apparatus including at least a spool, an actuation system for rotating a spool in a winding direction, and a brake system for braking a rotation of the drum. A cable is wound onto the spool. An impactor mass is attached to a free end of the cable. A release of the brake system causes a drop of the impactor mass by gravity, from a loaded condition, the actuating system subsequently rotating the spool to wind the cable onto the spool to put the impactor mass in a loaded condition.
1 . An impactor apparatus for use with a rotorcraft, comprising:
a reeling apparatus adapted to be transported by the rotorcraft, the reeling apparatus including at least
a spool,
an actuation system for rotating the spool in a winding direction, and
a brake system for braking a rotation of the spool;
a cable wound onto the spool; and
an impactor mass attached to a free end of the cable, the actuation system configured to lift a maximum weight being less than a weight of the impactor mass;
wherein a release of the brake system causes a drop of the impactor mass by gravity, from a loaded condition, the actuating system subsequently rotating the spool to wind the cable onto the spool to put the impactor mass in the loaded condition.
2 . A rotorcraft, comprising:
a fuselage;
a rotor rotatably mounted to the fuselage and configured for propelling the rotorcraft; and
an impactor apparatus mounted to the fuselage, the impactor apparatus having:
a reeling apparatus adapted to be transported by the rotorcraft, the reeling apparatus including at least
a spool,
an actuation system for rotating the spool in a winding direction, and
a brake system for braking a rotation of the spool;
a cable wound onto the spool; and
an impactor mass attached to a free end of the cable, the impactor mass adapted for demolition of an impacting site;
wherein a release of the brake system causes a drop of the impactor mass by gravity, from a loaded condition, the actuating system subsequently rotating the spool to wind the cable onto the spool to put the impactor mass in the loaded condition.
3 . The rotorcraft according to claim 2 , wherein the reeling apparatus includes a clutch unit between the actuation system and the spool.
4 . The rotorcraft according to claim 3 , wherein the clutch unit includes at least one spring exerting a biasing force between the actuation system and the spool.
5 . The rotorcraft according to claim 4 , wherein the at least one spring surrounds a shaft of the actuation system, and is between an abutment surface secured to the shaft and a coupler secured to the spool.
6 . The rotorcraft according to claim 5 , wherein the coupler is a disk inside a cavity of a core of the spool.
7 . The rotorcraft according to claim 4 , wherein the at least one spring is at least one Belleville spring.
8 . The rotorcraft according to claim 4 , wherein the clutch unit includes a tensioner for adjusting the biasing force applied by the spring.
9 . The rotorcraft according to claim 8 , wherein the tensioner has at least one fastener applying a pressure on the at least one spring.
10 . The rotorcraft according to claim 9 , wherein the at least one fastener is located inside a cavity of a core of the spool and is accessed from an exterior of the reeling apparatus.
11 . The rotorcraft according to claim 2 , wherein the actuation system includes an electric motor and a gear box.
12 . The rotorcraft according to claim 11 , wherein a rotational axis of the motor is transverse to a rotational axis of the spool.
13 . The rotorcraft according to claim 2 , wherein the brake system includes a strap selectively applying a braking force on a drum surface of the spool.
14 . The rotorcraft according to claim 13 , wherein the brake system includes a piston and at least one brake spring biasing the brake system to apply the braking force.
15 . The rotorcraft according to claim 14 , wherein the brake system includes a braking actuator operatively connected to the piston to apply a force against a biasing action of the at least one brake spring to release the braking force.
16 . The rotorcraft according to claim 14 , wherein the brake system includes a locking actuator operatively connected to the piston to apply a force concurrent with a biasing action of the at least one brake spring to lock the brake system.
17 . The rotorcraft according to claim 2 , wherein the reeling apparatus includes a cutter assembly adjacent to the cable and operable to section the cable.
18 . The rotorcraft according to claim 17 , wherein the cutter assembly has a frame defining a hole for passage of the cable therethrough, and a cutter in guillotine arrangement with the hole.
19 . The rotorcraft according to claim 18 , wherein the cutter is spring-loaded in a loaded condition, the cutter assembly having a detent mechanism for releasing the cutter from the loaded condition.
20 . The rotorcraft according to claim 2 , wherein an end of the cable opposite the free end is releasably laced to the spool.