Integral steering motor and collar for landing gear
A steering apparatus may comprise a steering collar, a first linear actuator, a first drive gear, a crankshaft, and a sun gear, wherein the sun gear is disposed within the collar, wherein the first drive gear is fixed to the crankshaft and coupled to the sun gear such that the collar rotates about the sun gear in response to rotation of the crankshaft, wherein the first linear actuator is coupled between the crankshaft and the collar.
1. A steering apparatus, comprising:
a steering collar including a sidewall and a portal through the sidewall;
a first linear actuator;
a first drive gear;
a crankshaft; and
a sun gear,
wherein the sun gear is disposed within the steering collar,
wherein the first drive gear is fixed to the crankshaft and coupled to the sun gear via the portal such that the steering collar rotates about the sun gear in response to rotation of the crankshaft,
wherein the first linear actuator is coupled between the crankshaft and the steering collar.
2. The steering apparatus of claim 1 , further comprising a second drive gear.
3. The steering apparatus of claim 1 , further comprising a second linear actuator coupled between the crankshaft and the steering collar.
4. The steering apparatus of claim 3 , wherein the second linear actuator is arranged with the first linear actuator in a V configuration.
5. The steering apparatus of claim 3 , wherein the second linear actuator is arranged with the first linear actuator in an in-line configuration.
6. A steering system for an aircraft comprising:
a strut cylinder;
a strut piston; and
a steering apparatus comprising:
a steering collar coupled to the strut cylinder, the steering collar including a sidewall and a portal through the sidewall;
a first linear actuator;
a first drive gear;
a crankshaft; and
a sun gear fixed to the strut cylinder,
wherein the sun gear is disposed within the steering collar,
wherein the first drive gear is fixed to the crankshaft and coupled to the sun gear via the portal such that the steering collar rotates about the sun gear in response to rotation of the crankshaft,
wherein the first linear actuator is coupled between the crankshaft and the steering collar.
7. The steering system of claim 6 , further comprising a second drive gear.
8. The steering system of claim 6 , further comprising a second linear actuator coupled between the crankshaft and the steering collar.
9. The steering system of claim 8 wherein the second linear actuator is arranged with the first linear actuator in a V configuration.
10. The steering system of claim 8 , wherein the second linear actuator is arranged with the first linear actuator in an in-line configuration.
11. The steering system of claim 6 , wherein the steering collar further comprises a retention feature opposite an upper surface of the steering collar and configured to retain the sun gear within the steering collar.
12. The steering system of claim 11 , wherein the steering collar includes a reinforced portion at the upper surface, wherein the reinforced portion abuts a shoulder of the strut cylinder generating a contact therebetween which inhibits the steering collar from translating axially upward along the strut cylinder.
13. An aircraft comprising:
a plurality of landing gear; and
a steering system coupled to at least one of the landing gear, the steering system comprising:
a strut cylinder;
a strut piston; and
a steering apparatus comprising:
a steering collar coupled to the strut cylinder, the steering collar including a sidewall and a portal through the sidewall;
a torque link coupled to the steering collar;
a first linear actuator;
a first drive gear;
a crankshaft; and
a sun gear fixed to the strut cylinder,
wherein the sun gear is disposed within the steering collar,
wherein the first drive gear is fixed to the crankshaft and coupled to the sun gear via the portal such that the steering collar rotates about the sun gear in response to rotation of the crankshaft,
wherein the first linear actuator is coupled between the crankshaft and the steering collar.
14. The aircraft of claim 13 , further comprising a second drive gear.
15. The aircraft of claim 13 , further comprising a second linear actuator coupled between the crankshaft and the steering collar.
16. The aircraft of claim 15 , wherein the second linear actuator is arranged with the first linear actuator in a V configuration.
17. The aircraft of claim 15 , wherein the second linear actuator is arranged with the first linear actuator in an in-line configuration.