Air vehicle assembly initialization and ejection

Patent metadata

Field	Value
Publication number	US-12509244-B2
Application number	US-202418612033-A
Country	US
Kind code	B2
Filing date	Mar 21, 2024
Priority date	Mar 21, 2024
Publication date	Dec 30, 2025
Grant date	Dec 30, 2025

Abstract

An air vehicle assembly initialization and ejection system includes a canister configured to contain an air vehicle assembly, where the air vehicle assembly includes an onboard electronic system and at least one squib for ejecting the air vehicle assembly from the canister. The system further includes a magazine having a canister position configured to contain the canister. The system further includes a first signal path providing electrical communication of a first control signal between the canister position and the canister, the first control signal for causing the onboard electronic system to power up, and a second signal path providing electrical communication of a second control signal between the canister position and the canister, the second control signal for causing the at least one squib to detonate.

First claim

What is claimed is:

1 . An air vehicle assembly initialization and ejection system comprising:
a canister configured to contain an air vehicle assembly, the air vehicle assembly including an onboard electronic system and at least one squib for ejecting the air vehicle assembly from the canister; a magazine including a canister position configured to contain the canister; a first signal path providing electrical communication of a first control signal between the canister position and the canister, the first control signal for causing the onboard electronic system to power up; and a second signal path providing electrical communication of a second control signal between the canister position and the canister, the second control signal for causing the at least one squib to detonate.

2 . The system of claim 1 , comprising an electrical circuit board for conducting the first signal path from the magazine to the canister position and the canister.

3 . The system of claim 2 , wherein the magazine includes a retaining plate for interfacing the magazine to a dispensing platform, wherein the electrical circuit board is on the retaining plate.

4 . The system of claim 1 , wherein the second signal path is electrically isolated from the first signal path.

5 . The system of claim 1 , comprising a controller configured to provide the first control signal to the canister along the first signal path, and to provide the second control signal to the canister along the second signal path.

6 . The system of claim 5 , wherein the controller is further configured to provide the first control signal after providing the second control signal.

7 . The system of claim 1 , further comprising the onboard electronic system, wherein the onboard electronic system includes a latching circuit, a switch coupled to the latching circuit, a power supply coupled to the switch, and a microcontroller coupled to the power supply.

8 . The system of claim 7 , wherein the latching circuit is configured to close the switch responsive to the second control signal, and wherein the switch conducts power from an energy storage device to the power supply for causing the microcontroller to become operational.

9 . The system of claim 1 , wherein the air vehicle assembly includes an inertial measurement unit (IMU) configured to track attitude and orientation of the air vehicle assembly prior to and through an ejection event.

10 . The system of claim 9 , wherein the IMU is powered up responsive to the first control signal.

11 . The system of claim 1 , further comprising the air vehicle assembly.

12 . An air vehicle assembly comprising:
an onboard electronic system including a latching circuit, a switch coupled to the latching circuit, a power supply coupled to the switch, and a microcontroller coupled to the power supply; at least one squib for ejecting the air vehicle assembly from a canister; a first signal path providing electrical communication of a first control signal between the canister and the at least one squib; and a second signal path providing electrical communication of a second control signal between the canister and the onboard electronic system.

13 . The air vehicle assembly of claim 12 , wherein the onboard electronic system is configured to be powered up responsive to the second control signal and prior to ejection of the air vehicle assembly from a canister.

14 . The air vehicle assembly of claim 12 , wherein the latching circuit is configured to close the switch responsive to the second control signal, and wherein the switch conducts power from an energy storage device to the power supply, thereby causing the microcontroller to become operational.

15 . The air vehicle assembly of claim 12 , wherein the at least one squib is configured to detonate responsive to the first control signal.

16 . The air vehicle assembly of claim 12 , comprising an inertial measurement unit (IMU) configured to track attitude and orientation of the air vehicle assembly prior to and through an ejection event.

17 . An air vehicle assembly initialization and ejection system comprising:
a canister configured to contain an air vehicle assembly, the air vehicle assembly including an onboard electronic system and at least one squib for ejecting the air vehicle assembly from the canister; a magazine including a canister position configured to contain the canister; and a controller configured to provide a first control signal to the canister along a first signal path, and to provide a second control signal to the canister along a second signal path, the first signal path providing electrical communication of the first control signal between the canister position and the canister, the second signal path providing electrical communication of the second control signal between the canister position and the canister.

18 . The system of claim 17 , wherein the second control signal is delayed with respect to the first control signal, the second control signal configured to cause the at least one squib to detonate, and wherein the second control signal is configured to cause application of power to the onboard electronic system prior to squib detonation.

19 . The system of claim 17 , further comprising the onboard electronic system, wherein the onboard electronic system includes a latching circuit, a switch coupled to the latching circuit, a power supply coupled to the switch, and a microcontroller coupled to the power supply.

20 . The system of claim 19 , wherein the latching circuit is configured to close the switch responsive to the second control signal, and wherein the switch conducts power from an energy storage device to the power supply for causing the microcontroller to become operational.

Assignees

• Bae Sys Inf & Elect Sys Integ

Inventors

• Hall Matthew M
• Knotts Michael E
• Sacco Bernard A
• Wendell Ross J
• Mitchell John A
• Chernick John D

Classifications

• B64U70/50

  Launching from storage containers, e.g. from submarine missile tubes · CPC title

• F41F1/00

  Launching apparatus for projecting projectiles or missiles from barrels, e.g. cannons (F41F3/00 takes precedence); Harpoon guns · CPC title

• B64F1/04 Primary

  for launching aircraft · CPC title

• B64U50/15 Primary

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