An electronic parachute deployment system including an electronic actuator, a control module, a deployment actuator, and a release mechanism. A parachute is positioned on a payload device, such as a racecar, to slow or stop the payload upon receipt of an electronic deployment activation signal. The electronic deployment signal is verified, including determining proper voltage and source. The deployment system includes multiple redundancies including mechanical deployment redundancy, remote deployment redundancy, and power supply redundancy. The control module responsible for monitoring deployment includes indicators and sensors to indicate a status, operation, or mode relative to the operability of the payload device, relative to components of the release mechanism, and relative to the parachute deployment.

An electronic parachute deployment system including an electronic actuator, a control module, a deployment actuator, and a release mechanism. A parachute is positioned on a payload device, such as a racecar, to slow or stop the payload upon receipt of an electronic deployment activation signal. The electronic deployment signal is verified, including determining proper voltage and source. The deployment system includes multiple redundancies including mechanical deployment redundancy, remote deployment redundancy, and power supply redundancy. The control module responsible for monitoring deployment includes indicators and sensors to indicate a status, operation, or mode relative to the operability of the payload device, relative to components of the release mechanism, and relative to the parachute deployment.

An electronic parachute deployment system including an electronic actuator, a control module, a deployment actuator, and a release mechanism. A parachute is positioned on a payload device, such as a racecar, to slow or stop the payload upon receipt of an electronic deployment activation signal. The electronic deployment signal is verified, including determining proper voltage and source. The deployment system includes multiple redundancies including mechanical deployment redundancy, remote deployment redundancy, and power supply redundancy. The control module responsible for monitoring deployment includes indicators and sensors to indicate a status, operation, or mode relative to the operability of the payload device, relative to components of the release mechanism, and relative to the parachute deployment.

A cone brake no-back includes an input no-back disk, an output no-back disk; and a no-back ball ramp mechanism operably connected to the input no-back disk and the output no back disk. An input no-back cone is operably connected to and supportive of the input no-back disk. The input no-back cone is axially loaded by an input no-back spring. An output no-back cone is operably connected to and supportive of the output no-back disk. The output no-back cone is axially loaded by an output no-back spring. A no-back input shaft is operably connected to the input no-back disk and the output no back disk, and a no-back output shaft is operably connected to the output no back disk.

An automobile comprising a cooling duct that extends to underneath the automobile to channel cooling air to a component of the automobile when the automobile is in motion is provided. A restriction located within the cooling duct that is moveable from a first position, in which airflow to the component is substantially unimpeded, to a second position in which the airflow to the component is substantially impeded, when the automobile is in motion is further provided. The automobile generates more downforce when the restriction is in the second position versus the first position. A control unit configured to select the position of the restriction to control the downforce generated by the automobile if the temperature of the component is below a predetermined level, and to select the first position for the restriction if the temperature of the component is above the predetermined level, is also provided.

An automobile comprising a cooling duct that extends to underneath the automobile to channel cooling air to a component of the automobile when the automobile is in motion is provided. A restriction located within the cooling duct that is moveable from a first position, in which airflow to the component is substantially unimpeded, to a second position in which the airflow to the component is substantially impeded, when the automobile is in motion is further provided. The automobile generates more downforce when the restriction is in the second position versus the first position. A control unit configured to select the position of the restriction to control the downforce generated by the automobile if the temperature of the component is below a predetermined level, and to select the first position for the restriction if the temperature of the component is above the predetermined level, is also provided.

An active wing apparatus (100) configured to be attached to a boot lid of a motor vehicle, the apparatus (100) comprising a wing assembly (120) configured to reversibly deploy in a first direction from a stowed condition to a deployed condition, the apparatus (100) further comprising anchor means (113L,113R) configured releasably to couple the apparatus (100) to a structural member being a portion of the vehicle body (50B) other than the boot lid, when the apparatus transitions from the stowed to the deployed condition.

An apparatus configured to control downforce is provided. The apparatus includes a piezoelectric bellow configured to generate airflow, a power controller configured to output a signal to actuate the piezoelectric bellow; and a controller configured to control the power controller based on vehicle dynamics information.

An apparatus configured to control downforce is provided. The apparatus includes a piezoelectric bellow configured to generate airflow, a power controller configured to output a signal to actuate the piezoelectric bellow; and a controller configured to control the power controller based on vehicle dynamics information.

Braking systems for aircraft are disclosed. An example braking system includes a brake pad movably coupled to a lower section of a fuselage of the aircraft. The brake pad is movable between a stowed position and a deployed position. An actuator is configured to deploy the brake pad from the fuselage during an emergency braking event. The brake pad to engage a surface of a runway and increase frictional force to reduce a speed of the aircraft during the emergency braking event.