Aircraft tow system
Disclosed is an unmanned, autonomous, cargo transport system comprising at least one towed aircraft coupled to a tractor aircraft for inflight towing.
1 . A towing assembly for an aircraft, comprising:
a cable connector assembly configured to be connected to a towing element, comprising:
a first base component;
a hook configured to be releasably connected to the towing element;
a hook release arm coupled to the hook, the hook release arm being configured to disengage the hook from the towing element when activated; and
an electrical actuator mechanically coupled to the hook release arm, wherein the electrical actuator is configured to activate the hook release arm and disengage the hook from the towing element in response to an electronic signal;
an aircraft connector assembly configured to be connected to an end of the aircraft, comprising:
a second base component; and
a connector attached to the second base component configured to be connected to the end of the aircraft; and
a load cell array coupled between the first base component and the second base component.
2 . The towing assembly of claim 1 , wherein the electrical actuator includes one or more solenoids mechanically coupled to the hook release arm.
3 . The towing assembly of claim 1 , wherein the electrical actuator is configured to active the hook release arm by mechanically pulling on the hook release arm, which in turn disengages the hook from the towing element.
4 . The towing assembly of claim 1 , further comprising a mechanical actuator connected to the hook release arm, wherein the mechanical actuator is configured to activate the hook release arm and disengage the hook from the towing element.
5 . The towing assembly of claim 1 , wherein the load cell array includes one or more measurement devices for assessing magnitude and direction of tensing in the towing element.
6 . The towing assembly of claim 1 , further comprising a switch circuit coupled to the electrical actuator, wherein the switch circuit includes a switch operable by an operator to provide the electronic signal to activate the electrical actuator.
7 . The towing assembly of claim 6 , wherein the switch circuit is coupled to the electrical actuator via a data communication network.
8 . The towing assembly of claim 6 , wherein the switch is located in a cockpit of the aircraft.
9 . The towing assembly of claim 1 , wherein the load cell array includes a plurality of load cells oriented in different directions.
10 . The towing assembly of claim 9 , wherein the load cells provide freedom of movement between the cable connector assembly and the aircraft connector assembly in the different directions.
11 . The towing assembly of claim 9 , wherein the load cell array includes six load cells configured to provide six degrees of freedom of movement between the cable connector assembly and the aircraft connector assembly.
12 . An aircraft towing system, comprising:
a towing element configured to be attached between a tractor aircraft and a towed aircraft;
a first towing assembly connected to a tail end of the tractor aircraft, the first towing assembly comprising:
a first cable connector assembly configured to be connected to a first end of the towing element, comprising:
a first base component;
a first hook configured to be releasably connected to the towing element;
a first hook release arm coupled to the first hook, the first hook release arm being configured to disengage the first hook from the towing element when activated; and
a first electrical actuator mechanically coupled to the first hook release arm, wherein the first electrical actuator is configured to activate the first hook release arm and disengage the first hook from the towing element in response to a first electronic signal;
a first aircraft connector assembly configured to be connected to the tail end of the tractor aircraft, comprising:
a second base component; and
a first connector attached to the second base component configured to be connected to the tail end of the tractor aircraft;
a first load cell array coupled between the first base component and the second base component;
a second towing assembly connected to a nose end of the towed aircraft, the second towing assembly comprising:
a second cable connector assembly configured to be connected to a second end of the towing element, comprising:
a third base component;
a second hook configured to be releasably connected to the towing element;
a second hook release arm coupled to the second hook, the second hook release arm being configured to disengage the second hook from the towing element when activated; and
a second electrical actuator mechanically coupled to the second hook release arm, wherein the second electrical actuator is configured to activate the second hook release arm and disengage the second hook from the towing element in response to a second electronic signal;
a second aircraft connector assembly configured to be connected to the nose end of the towed aircraft, comprising:
a fourth base component; and
a second connector attached to the fourth base component configured to be connected to the nose end of the towed aircraft; and
a second load cell array coupled between the third base component and the fourth base component.
13 . The aircraft towing system of claim 12 , wherein the first and second electrical actuators include one or more solenoids mechanically coupled to the first and second hook release arms, respectively.
14 . The aircraft towing system of claim 12 , wherein the first electrical actuator is configured to active the first hook release arm by mechanically pulling on the first hook release arm, which in turn disengages the first hook from the first end of the towing element.
15 . The aircraft towing system of claim 12 , wherein the second electrical actuator is configured to active the second hook release arm by mechanically pulling on the second hook release arm, which in turn disengages the second hook from the second end of the towing element.
16 . The aircraft towing system of claim 12 , wherein the first electrical actuator and the second electrical actuator are operated independently.
17 . The aircraft towing system of claim 12 , further comprising:
a first switch circuit coupled to the first electrical actuator, wherein the first switch circuit includes a first switch operable by an operator in the tractor aircraft to provide the first electronic signal to activate the first electrical actuator; and
a second switch circuit coupled to the second electrical actuator, wherein the second switch circuit includes a second switch operable by an operator in the towed aircraft to provide the second electronic signal to activate the second electrical actuator.
18 . The aircraft towing system of claim 17 , wherein the second switch circuit is operable by the operator in the tractor aircraft via a data communication network between the tractor aircraft and the towed aircraft.
19 . The aircraft towing system of claim 17 , wherein the first switch circuit is operable by the operator in the towed aircraft via a data communication network between the tractor aircraft and the towed aircraft.
20 . A towed aircraft system, comprising:
a tractor aircraft;
a towed aircraft;
a towing element configured to be attached between the tractor aircraft and the towed aircraft;
a first towing assembly connected to a tail end of the tractor aircraft, the first towing assembly comprising:
a first cable connector assembly configured to be connected to a first end of the towing element, comprising:
a first base component;
a first hook configured to be releasably connected to the towing element;
a first hook release arm coupled to the first hook, the first hook release arm being configured to disengage the first hook from the towing element when activated; and
a first electrical actuator mechanically coupled to the first hook release arm, wherein the first electrical actuator is configured to activate the first hook release arm and disengage the first hook from the towing element in response to a first electronic signal;
a first aircraft connector assembly configured to be connected to the tail end of the tractor aircraft, comprising:
a second base component; and
a first connector attached to the second base component configured to be connected to the tail end of the tractor aircraft;
a first load cell array coupled between the first base component and the second base component;
a second towing assembly connected to a nose end of the towed aircraft, the second towing assembly comprising:
a second cable connector assembly configured to be connected to a second end of the towing element, comprising:
a third base component;
a second hook configured to be releasably connected to the towing element;
a second hook release arm coupled to the second hook, the second hook release arm being configured to disengage the second hook from the towing element when activated; and
a second electrical actuator mechanically coupled to the second hook release arm, wherein the second electrical actuator is configured to activate the second hook release arm and disengage the second hook from the towing element in response to a second electronic signal;
a second aircraft connector assembly configured to be connected to the nose end of the towed aircraft, comprising:
a fourth base component; and
a second connector attached to the fourth base component configured to be connected to the nose end of the towed aircraft; and
a second load cell array coupled between the third base component and the fourth base component.