Constant speed drive apparatus for aircraft generator and traction speed change apparatus

• US 6,312,358 B1
• Filed: 05/30/2000
• Issued: 11/06/2001
• Est. Priority Date: 05/21/1999
• Status: Expired due to Term

• Current Assignee: Kawasaki Jukogyo Kabushiki Kaisha
• Original Assignee: Advanced Technology Institute of Commuter-Helicopter, Ltd.
• Inventors: Goi, Tatsuhiko, Kawakami, Kouji, Yamakawa, Eiichi
• Primary Examiner(s): Marmor, Charles A
• Assistant Examiner(s): HO, HA DINH
• Application Number:
  US09/583,167
• Time in Patent Office: 525 Days
• Field of Search: 477/37, 477/42, 475/208, 475/214, 475/216, 476/4, 476/11, 476/43, 476/41
• US Class Current: 477/37
• CPC Class Codes: F16H 15/38 with two members B having hollow toroid surfaces opposite to each other, the member or members A being adjustably mounted between the surfaces
• CPC Class Codes: F16H 61/664 Friction gearings

Abstract

A constant speed drive apparatus for an aircraft generator comprises an input shaft for receiving drive torque from an aircraft engine, a traction speed change mechanism of continuously-variable speed change ratio which is coupled to the input shaft, an output shaft for supplying the aircraft generator with drive torque which is changed in speed by the traction speed change mechanism, and a control computer for controlling the speed change ratio of the traction speed change mechanism to maintain the output shaft at a predetermined rotational frequency. With such constitution it is possible to achieve a small and lightweight constant speed drive apparatus having a high transmission efficiency.

Claims

1. A constant speed drive apparatus for an aircraft generator, comprising:

an input shaft for receiving drive torque from an aircraft engine;

a traction speed change mechanism having a continuously-variable speed change ratio, said traction speed change mechanism being coupled to said input shaft;

an output shaft for supplying the aircraft generator with drive torque, said output shaft being arranged to have a rotational speed varied by said traction speed change mechanism; and

a rotational-frequency controlling mechanism for controlling the speed change ratio of said traction speed change mechanism so as to maintain said output shaft at a predetermined rotational frequency;

wherein said traction speed change mechanism includes;

an input disk interlocked to said input shaft;

an output disk interlocked to said output shaft;

transmission rollers disposed between said input disk and said output disk;

yoke members for supporting said transmission rollers such that said transmission rollers are pivotable about an axis perpendicular to an axis of rotation of each of said transmission rollers and an axis of rotation of said input disk; and

and actuator for pulling said yoke members along the axis of rotation of said input disk so as to draw said transmission rollers toward said input disk to generate a pressing force of said transmission rollers.

2. A constant speed drive apparatus of claim 1, wherein said rotational-frequency controlling mechanism includes:

a rotational-frequency detecting mechanism for detecting a rotational frequency of said output shaft and generating a detection signal; and

a control circuit for controlling the speed change ratio of said traction speed change mechanism based on the detection signal generated by and received from said rotational-frequency detecting mechanism.

3. The constant speed drive apparatus of claim 2, wherein engine status values indicating an operating status of the aircraft engine are inputted to said control circuit, said control circuit being operable to estimate variations in the rotational frequency of said input shaft on the basis of the engine status values to stabilize the rotational frequency of said output shaft.

4. A power generating apparatus for an aircraft comprising:

said constant speed drive apparatus of claim 1; and

a generator driven by said output shaft to generate electric power.

5. A traction speed change mechanism comprising:

an input disk interlocked to a torque input shaft;

an output disk interlocked to a torque output shaft;

transmission rollers disposed between said input disk and said output disk;

yoke members for supporting said transmission rollers such that said transmission rollers are pivotable about an axis perpendicular to an axis of rotation of each of said transmission rollers and an axis of rotation of said input disk; and

an actuator for pulling said yoke members along the axis of rotation of said input disk so as to draw said transmission rollers toward said input disk to generate a pressing force of the transmission rollers.

6. A constant speed drive apparatus for an aircraft generator, comprising:

an input shaft for receiving drive torque from an aircraft engine;

a traction speed change mechanism having a continuously-variable speed change ratio, said traction speed change mechanism being coupled to said input shaft;

an output shaft for supplying the aircraft generator with drive torque, said output shaft being arranged to have a rotational speed varied by said traction speed change mechanism, said output shaft being directly coupled to the aircraft generator; and

a rotational-frequency controlling mechanism for controlling the speed change ratio of said traction speed change mechanism so as to maintain said output shaft at a predetermined rotational frequency;

wherein said traction speed change mechanism is a single cavity type and includes;

an input disk interlocked to the input shaft;

an output disk having an outer diameter smaller than an outer diameter of said input disk, said output disk being interlocked to said output shaft;

transmission rollers disposed between said input disk and said output disk; and

a pressing force generating mechanism for increasing a pressure of said transmission rollers against said input disk and said output disk, said pressing force generating mechanism including yoke members for supporting said transmission rollers and an actuator connected to said yoke members for pulling said yoke members along an axis of rotation of said input disk and said output disk; and

wherein the aircraft generator is operable to be driven in a state in which said traction speed change mechanism is accelerated up to a speed higher than a rotational frequency of said input shaft.

7. A constant speed drive apparatus of claim 6, wherein said rotational-frequency controlling mechanism includes:

a rotational-frequency detecting mechanism for detecting a rotational frequency of said output shaft and generating a detection signal; and

a control circuit for controlling the speed change ratio of said traction speed change mechanism based on the detection signal generated by and received from said rotational-frequency detecting mechanism.

8. A power generating apparatus for an aircraft comprising:

said constant speed drive apparatus of claim 6; and

a generator driven by said output shaft to generate electric power.

9. A constant speed drive apparatus for an aircraft generator, comprising:

an input shaft for receiving drive torque from an aircraft engine;

a traction speed change mechanism having a continuously-variable speed change ratio, said traction speed change mechanism being coupled to said input shaft;

an output shaft for supplying the aircraft generator with drive torque, said output shaft being arranged to have a rotational speed varied by said traction speed change mechanism, said output shaft being directly coupled to a drive shaft of the aircraft generator; and

a rotational-frequency controlling mechanism for controlling the speed change ratio of said traction speed change mechanism so as to maintain said output shaft at a predetermined rotational frequency, said rotational-frequency controlling mechanism including;

a rotational-frequency detecting mechanism for detecting a rotational frequency of said output shaft and generating a detection signal; and

a control circuit for controlling the speed change ratio of said traction speed change mechanism based on the detection signal generated by and received from said rotational-frequency detecting mechanism;

wherein said traction speed change mechanism is a single cavity type and includes;

an input disk interlocked to the input shaft;

an output disk having an outer diameter smaller than an outer diameter of said input disk, said output disk being interlocked to said output shaft;

transmission rollers disposed between said input disk and said output disk; and

a pressing force generating mechanism for increasing a pressure of said transmission rollers against said input disk and said output disk; and

wherein the aircraft generator is operable to be driven in a state in which said traction speed change mechanism is accelerated up to a speed higher than a rotational frequency of said input shaft, and engine status values indicating an operating status of the aircraft engine are inputted to said control circuit, said control circuit being operable to estimate variations in the rotational frequency of said input shaft based on the engine status values to stabilize the rotational frequency of said output shaft.