Retractable aerodynamic structures for cargo bodies and methods of controlling positioning of the same
A system that has electrically or electro-pneumatically actuated aerodynamic structures. An electric or electro-pneumatic actuator is employed, which receives signals from an existing anti-lock braking system (ABS) controller to determine when actuation occurs. Other systems are also provided that feature electric or electro-pneumatic actuation, including underbody skirts and scoops, as well as inflatable tractor-trailer gap sealing devices, adjustable tractor-trailer gap sealing flaps and inflatable trailer upper streamlining devices. Electronic control units (ECUs) for aerodynamic system control interfacing with alternate sensors for calculating speed are also provided. Satellite navigation, platooning awareness and managed pressure reserve capability can be employed with the aerodynamics ECU.
1. A system comprising:
one or more actuators operatively connected to at least one panel of an aerodynamic structure to move the aerodynamic structure from a deployed position to a retracted position or from a retracted position to a deployed position;
one or more electronic control units that process sensor signals to analyze motion of a vehicle and control the one or more actuators based on the motion of the vehicle and control logic; and
one or more mechanisms that bias the aerodynamic structure into the deployed position or the retracted position when the one or more actuators are not actuated,
wherein two or more panels of the aerodynamic structure are operatively connected so that movement of one panel causes movement in another panel.
2. The system of claim 1 wherein the aerodynamic structure is rear-facing, and wherein the aerodynamic structure comprises at least an upper panel, a first side panel, and a second side panel.
3. The system of claim 2 wherein:
the upper panel, the first side panel, and the second side panel each mounted to a door of a cargo body of the vehicle and move between a folded position on the door in the retracted position and the deployed position,
in the deployed position, the aerodynamic structure has an internal cavity defined by the upper panel, the first side panel, and the second side panel, and
a linkage assembly is operatively connected between the upper panel and the first side panel or the second side panel so that movement of the first side panel or the second side panel causes movement of the linkage assembly in response thereto and movement of the upper panel in response to the movement of the linkage assembly.
4. The system as set forth in claim 2 wherein:
the aerodynamic structure further comprises one or more bottom panels,
the upper panel, the one or more bottom panels, the first side panel, and the second side panel each mounted to a door of the cargo body and move between a folded position on the door in the retracted position and the deployed position,
in the deployed position, the aerodynamic structure has an internal cavity defined by the upper panel, the one or more bottom panels, the first side panel, and the second side panel, and
a linkage assembly is operatively connected between the upper panel and the one or more bottom panels so that movement of the one or more bottom panels causes movement of the linkage assembly in response thereto and movement of the upper panel in response to the movement of the linkage assembly.
5. The system of claim 2 wherein the one or more actuators are operatively connected between a door of a cargo body of the vehicle and the first side panel or the second side panel.
6. The system of claim 2 wherein the one or more actuators are operatively connected between a door of a cargo body of the vehicle and the upper panel.
7. The system of claim 1 further comprising an electronic latch mechanism operatively connected to the one or more electronic control units, and wherein the electronic latch mechanism releases based on a signal received from the one or more electronic control units.
8. The system of claim 7 wherein the aerodynamic structure is configured to move to the deployed position or the retracted position under a biasing force supplied by the one or more mechanisms upon release of the electronic latch mechanism.
9. The system of claim 7 wherein the aerodynamic structure is secured in the retracted position when the electronic latch mechanism is in a latched state and the aerodynamic structure is biased into the deployed position by the one or more mechanisms when the electronic latch mechanism is in a released state.
10. The system of claim 7 wherein the aerodynamic structure is secured in the deployed position when the electronic latch mechanism is in a latched state and the aerodynamic structure is biased into the retracted position by the one or more mechanisms when the electronic latch mechanism is in a released state.
11. The system of claim 7 further comprising an indicator, wherein the indicator displays feedback from the electronic latch mechanism or the one or more actuators to alert a user of a position of the aerodynamic structure.
12. The system of claim 1 wherein the one or more powered actuators is a motor-driven cable winch system that automatically pulls one or more panels of the aerodynamic structure into the retracted position based upon a signal received from the one or more electronic control units.
13. The system of claim 1 wherein the one or more mechanisms that bias the aerodynamic structure comprise one or more gas springs or torsion springs.
14. The system of claim 1 wherein one or more of the one or more electronic control units is an antilock braking system controller.
15. The system of claim 1 wherein one or more of the one or more electronic control units is connected to a wheel speed sensor.
16. The system of claim 1 wherein one or more of the one or more electronic control units includes a built-in accelerometer to analyze the motion of the vehicle.
17. The system of claim 1 wherein one or more of the one or more electronic control units includes a built-in GPS to analyze the motion of the vehicle.
18. The system of claim 1 wherein one or more of the one or more of the electronic control units is connected to a first pressure sensor and a second pressure sensor, wherein the first pressure sensor is located at a rear of the aerodynamic structure and the second pressure sensor is located in an airstream, wherein the first pressure sensor and the second pressure sensor calculates aerodynamic pressure drag at the rear of the aerodynamic structure.
19. The system of claim 1 wherein one or more of the one or more electronic control units is connected to an optical reader that calculates the motion of the vehicle by viewing displacement of the ground relative to the vehicle.
20. The system of claim 1 wherein the one or more actuators includes one or more of: a linear pneumatic cylinder, a pneumatic contracting muscle, a pneumatic expanding bladder, an indirect drive linear electric motor, a linear hydraulic cylinder, an electric winch, a rotary pneumatic motor, or a rotary electric motor.
21. The system of claim 1 , wherein the actuator is operatively connected to the at least one panel by a linkage.
22. A system comprising:
one or more actuators operatively connected to at least one panel of an aerodynamic structure to control positioning of the aerodynamic structure between one of a deployed position or a retracted position;
one or more electronic control units that process sensor signals to analyze motion of the vehicle and control the one or more actuators based on motion of the vehicle and control logic;
one or more mechanisms that bias the aerodynamic structure into the other of the deployed position or the retracted position,
wherein two or more panels of the aerodynamic structure are operatively connected so that movement of one panel causes movement in another panel,
wherein the aerodynamic structure comprises at least one upper panel and at least two side panels, and
wherein the one or more actuators are operatively connected between a door of a cargo body of the vehicle and the at least one upper panel or the at least two side panels.
23. A system comprising:
one or more actuators operatively connected to at least one panel of an aerodynamic structure by a linkage to move the aerodynamic structure from a deployed position to a retracted position or from a retracted position to a deployed position;
one or more electronic control units that process sensor signals to analyze motion of a vehicle and control the one or more actuators based on the motion of the vehicle and control logic; and
one or more mechanisms that bias the aerodynamic structure into the deployed position or the retracted position when the one or more actuators are not actuated.
24. The system of claim 23 , wherein two or more panels of the aerodynamic structure are operatively connected so that movement of one panel causes movement in another panel.