Drone launch systems and methods

Patent metadata

Field	Value
Publication number	US-9969491-B2
Application number	US-201514843329-A
Country	US
Kind code	B2
Filing date	Sep 2, 2015
Priority date	Sep 2, 2015
Publication date	May 15, 2018
Grant date	May 15, 2018

Abstract

A drone launch system includes a canister defining an internal cavity, and a drone positioned within the internal cavity in a stowed state. The drone is configured to be ejected from the canister and transition from the stowed state into a deployed state outside of the canister. A method for launching a drone, the method includes positioning the drone in a stowed state in an internal cavity of a canister, ejecting the drone from the canister, and transitioning the drone into a deployed state after the ejecting operation.

First claim

What is claimed is:

1. A drone launch system, comprising:
a canister defining an internal cavity; and
a drone positioned within the internal cavity in a stowed state, wherein the drone is configured to be ejected from the canister and transition from the stowed state into a deployed state outside of the canister, wherein the drone comprises:
a main housing and at least one arm having at least one propulsion system, wherein the at least one arm is folded into a collapsed position in the stowed state, and wherein the at least one arm extends outwardly from the main housing in the deployed state, wherein the at least one arm comprises a fixed beam that connects to an extension beam through a hinge, wherein the extension beam is rearwardly folded in the stowed state, and wherein the extension beam moves about the hinge into an extended position in the deployed state; and
at least one connection member that is configured to connect to and restrain the extension beam in the stowed state, wherein the connection member is configured to release the extension beam as the drone transitions from the stowed state to the deployed state.

2. The drone launch system of claim 1 , wherein the canister is water-tight in a closed position in which the drone is stowed within the internal cavity.

3. The drone launch system of claim 1 , wherein the canister is buoyant and configured to float on a surface of water when the drone is in the stowed state within the internal cavity.

4. The drone launch system of claim 1 , wherein the drone further comprises at least one deployable landing leg, wherein the at least one deployable landing leg extends into a deployed position as the drone transitions from the stowed state to the deployed state.

5. The drone launch system of claim 1 , further comprising a launch vehicle secured to the drone within the internal cavity.

6. The drone launch system of claim 5 , wherein the launch vehicle comprises a plurality of fins, and wherein the canister comprises a plurality of fin guides that retain the plurality of fins when the launch vehicle is stowed within the canister.

7. The drone launch system of claim 5 , wherein the launch vehicle comprises at least one blade holder configured to restrain at least a portion of a propulsion system of the drone in the stowed position.

8. The drone launch system of claim 5 , wherein the launch vehicle activates to eject the launch vehicle and the drone from the internal cavity in response to detection of a condition of the drone launch system.

9. The drone launch system of claim 8 , wherein the launch vehicle comprises at least one sensor that is configured to detect the condition, and wherein the condition is one of an altitude, an acceleration, a velocity, a position relative to sea level, or a time from a launch of the canister from a platform.

10. The drone launch system of claim 5 , wherein the drone separates from the launch vehicle and transitions to the deployed state in response to detection of a condition of the drone.

11. The drone launch system of claim 10 , wherein the drone comprises at least one sensor configured to detect the condition, and wherein the condition is one of an altitude, an acceleration, a velocity, a position relative to sea level, or a time from a launch of the launch vehicle and the drone from the canister.

12. A drone launch system, comprising:
a canister defining an internal cavity;
a drone positioned within the internal cavity in a stowed state, wherein the drone is configured to be ejected from the canister and transition from the stowed state into a deployed state outside of the canister, wherein the drone comprises a main housing, a drone sensor, and a plurality of arms having a plurality of propulsion systems, wherein each of the plurality of arms is folded into a collapsed position in the stowed state, and wherein the each of the plurality of arms extends outwardly from the main housing in the deployed state; and
a launch vehicle secured to the drone within the internal cavity, wherein the launch vehicle activates to eject the launch vehicle and the drone from the internal cavity in response to detection of a first condition of the drone launch system, wherein the launch vehicle comprises a launch vehicle sensor that is configured to detect the first condition, wherein the first condition is one of a first altitude, a first acceleration, a first velocity, a first position relative to sea level, or a first time from a launch of the canister from a platform, wherein the drone separates from the launch vehicle and transitions to the deployed state in response to detection of a second condition of the drone, and wherein the drone sensor is configured to detect the second condition, wherein the second condition is one of a second altitude, a second acceleration, a second velocity, a second position relative to sea level, or a second time from a launch of the launch vehicle and the drone from the canister.

13. The drone launch system of claim 12 , wherein the launch vehicle comprises a plurality of fins, and wherein the canister comprises a plurality of fin guides that retain the plurality of fins when the launch vehicle is stowed within the canister.

14. The drone launch system of claim 12 , wherein the launch vehicle comprises a plurality of blade holders configured to restrain at least portions of the plurality of propulsion systems of the drone in the stowed position.

15. The drone launch system of claim 12 , wherein the drone further comprises a plurality of deployable landing legs, wherein the plurality of deployable landing legs extends into a deployed position as the drone transitions from the stowed state to the deployed state.

16. The drone launch system of claim 12 , wherein each of the plurality of arms comprises a fixed beam that connects to an extension beam through a hinge, wherein the extension beam is rearwardly folded in the stowed state, and wherein the extension beam swings about the hinge into an extended position in the deployed state.

17. The drone launch system of claim 16 , wherein the drone comprises a plurality of connection members, wherein each of the plurality of connection members is configured to connect to and restrain a respective one of the extension beams in the stowed state, wherein each of the plurality of connection members is configured to release the respective one of the extension beams as the drone transitions from the stowed state to the deployed state.

18. A drone launch system, comprising:
a canister defining an internal cavity;
a drone positioned within the internal cavity in a stowed state, wherein the drone is configured to be ejected from the canister and transition from the stowed state into a deployed state outside of the canister; and
a launch vehicle secured to the drone within the internal cavity, wherein the launch vehicle comprises at least one blade holder configured to restrain at least a portion of a propulsion system of the drone in the stowed position.

19. A drone launch system, comprising:
a canister defining an internal cavity and including a plurality of fin guides;
a drone positioned within the internal cavity in a stowed state, wherein the drone is configured to be ejected from the canister and transition from the stowed state into a deployed state outside of the canister; and
a launch vehicle secured to the drone within the internal cavity, wherein the launch vehicle includes a fuselage that retains a propulsion system and a plurality of fins, wherein the plurality of find guides retain the pl

Assignees

• Boeing Co

Inventors

• Strayer James David

Classifications

• B64U50/15

  using combustion exhausts other than turbojets or turbofans, e.g. using rockets, ramjets, scramjets or pulse-reactors · CPC title

• B64U80/70

  in containers (B64U80/60 takes precedence) · CPC title

• B64U80/84

  Waterborne vehicles · CPC title

• B64C5/06

  Fins (B64C5/08 takes precedence) · CPC title

• B64C2201/08

  Operations & Transport · mapped topic