GB2283471A - Helicopter stabilizer. - Google Patents

Abstract

A helicopter stabilizer within a supporting structure 1 secured to the helicopter fuselage opposes the main rotor torque. A cluster of gyroscopes 4 driven by air motors (3) (Fig 2) is mounted on a hollow vertical shaft (8) (Fig 1) and a pulley (5). Shaft (8) is freely rotatable in upper and lower bearings. Belts 14 connect pulley (5) to two pulleys 13 drivable by air motors (12) (Fig 4). Air supply to motors (12) is controlled by valves linked to rudder controls and main rotor de-coupling controls (Figs 7 - 9) to rotate pulleys 13 and hence pulley (5), which resists rotation, to generate a torque 15 about the axis of shaft (8). <IMAGE>

Description

HELICOPTER STAEILIZER.

Helicopter stabilizers are well known comprising mainly of tail rotors, replacing auto-gyro tail fins when main rotors became engine powered, Whereby tail rotor force moments offset main rotor force couples for fuselage stability.

Tail rotors require extended air frames,positioned to avoid fuselage rolling force couples,ship board space is limited for helicopters, military ground fire and tree canopied terrain hazard susceptable tail rotor blades.

According to the present invention there is provided a helicopter stab -iliz- comprising,a vertically pivoting torque generator containing pneumatically driven gyroscopes positioned for maximum torque,a transmission belt pulley mounted on the torque generator positioned for vertical axis rotation,a pair of pulley mounted gearboxes driven by variable speed dual rotation pneumatic motors,whereby the said pulleys displace by tracking when connected transmission belts are motion suppressed by the said torque generators torque action thereto also connected.A pair of transmission belts to connect the said pulleys.A fuselage mountable struc -ture to support the torque generator and pulley mounted gearboxes,a protec -tive cowling,strategically mailed and insulated against ice accretion.

A rotary air compressor,connected to a helicopter main rotor gearbox by a transmission shaft and couplings,component provisions of linkages,pipes, valves and related parts for air transmission from the said compressor to the helicopter stabilizer thereby controlling by manual and automatic means.

A specific embodiment of the invention will now be described by way of example with reference to the accompanying drawings in which: Figure 1 Shows a side view of the torque generator.

Figure 2 Shows a downward view of the torque generator partly dismantled.

Figure 3 Shows a side view of the pulley mounted gearbox,side removed.

Figure 4 Shows a downward view of the pulley mounted gearbox with motors disposed within.

Figure 5 A perspective view of the structured helicopter stabilizer is shown.

Figure 6 Shows the positions where the helicopter stabilizer and compressor are secured on a fuselage.

Figure 7 A perspective view of an air distribution valve is shown.

Figure 8 An end view section shows the position of valve outlets phased to opposing force couple balance under main rotor engine power.

Figure 9 An end view section shows the position of valve outlets phased to auto-rotation fuselage control.

Referring to the drawings,the helicopter stabilizer comprises of a torque generator Fig 1 and Fig 2 where pneumatic motors 3 are mounted with conically shaped gyroscopes 4 inserted into an encompassing two sheave pulley 5 where bearings receive the motor 3 shafts. A two part supporting block 6 and 7 secures the motors 3 when the block 6 is offered up with the tubular shaft 8 inserted,whereby the upper block 7 is lowered down the shaft 8 thereby securing the motors 3 when the block bolts 9 are secured.

Referring to the tubular shaft 8,the ends are fitted with both bearings and glands 10 for pivotal support and compressed air transfer to the middle of the shaft 8 outletting air through slots to an air distribution chamber 11 machined in the supporting blocks 6 and 7 supplying compressed air to the motors 3.

When the pulley 5 is driven by belts 14 the torque generator produces a torque action, the opposing re-action will not be found on a helicopter to which it is secured,but may be found within the rules of gyroscopic law.

The torque action is distributed fore and aft by belts 14 along the stabilizer 1 structure to pulley mounted gearboxes powered by pneumatic motors 12 shown in Fig 3 and Fig 4 whereby the pulleys 13 track along the motion reluctant belts 14 shown by arrows 15 in Fig 5 where the assembled helicopter stabilizer 1 is seen in perspective,the pulleys 13 mainly rotate in the opposite direction to the helicopter main rotor thereby winching against the reluctant belts 14 producing an opposing force couple to the force couple produced by a helicopter main rotor.

Air pipe connectors 16 inlet compressed air providing dual rotation to the motors 12,spent air outlets through ducting connectors 17 and may be seen in Figs 3 and 4.

The secured positions of the assembled stabilizer 1 and the air compressor 2 may be seen in the Fig 6 with deck winch access cut-outs 18 in the protective cowling,the Fig 5 perspective drawing shows the deck winch access in the form of a box within the assembled stabilizer 1 supportive structure and belt tensioners 20 adjacent to transmission belts 14 may also be seen.

An oil cooled rotary vane compressor or similar,connected to a main rotor gearbox by a transmission drive shaft,supplys compressed air to the stabilizer 1 through flexible pipes and valves.

Air conditioned air outlets from the compressor 2 piped to a cylinder on cylinder rotary air distribution valve shown in Fig 7,the outer lever mounted cylinder 24 pipe connects one inlet and two outlets,limited stop movement phase changes air transmission to the stabilizer 1,ranging from engine powered main rotor phase to auto-rotation phase ,shown in Fig 8 and Fig 9. The inner lever mounted cylinder 25 is controlled by rudder control thereto cable linked, thereby speed changing stabilizer 1 pulleys 13 in Fig 5, the pulleys 13 rotate in the opposite direction to main rotor rotation when engines drive the main rotor.

When the outer cylinder 24 is phase changed by a rotary shift by linked main rotor de-couple action, the pulleys 13 shown in Fig 5 will dual rotate controlling the force couple free fuselage in auto-rotation.The air distribution valve Fig 7 secures a collective pitch linked booster valve 21 adjusting force couple variations by air volume increase,balancing rotor and stabilizer 1 couples.In auto-rotation valve 21 in Fig 7 still functions in rotor overswing blade pitch suppression offset here by rudder control.

A bypass pipe direct from the compressor 2 to the motors 3 in Fig 1 spin the gyroscopes thereby generating torque in motion.The distribution valve Fig 7 producing stability and steerage may alternatively be linkaged for automatic force couple stabilizing balance where desired,whereby flight path changes,including rotor underswing free altitude climbing,may be acheived by traditional movable tail surfaces when flight path momentum suffices.

Claims (2)

CLAIMS.

1 A helicopter stabilizer comprising,a vertically pivoting torque generator containing pneumatically driven gyroscopes positioned for maximum torque ,a transmission belt pulley mounted on the torque generator positioned for vertical axis rotation,a pair of pulley mounted gearboxes driven by variable speed dual rotation pneumatic motors,whereby the said pulleys displace by tracking when connected transmission belts are motion suppressed by the said torque generators torque action thereto also connected.A pair of transmission belts to connect the said pulleys .A fuselage mountable structure to support the torque generator and pulley mounted gearboxes, a protective cowling, strategically mailed and insulated against ice accretion.

A rotary air compressor, connected to a helicopter main rotor gearbox by a transmission shaft and couplings,component provisions of linkages, pipes,valves and related parts for air transmission from the said compressor to the helicopter stabilizer thereby controlling by manual and automatic means.

2 A helicopter stabilizer substantially as described herein with reference to Figures 1-9 of the accompanying drawing.