Systems and methods for controlling a magnitude of a sonic boom

Patent metadata

Field	Value
Publication number	US-9561847-B2
Application number	US-201414176865-A
Country	US
Kind code	B2
Filing date	Feb 10, 2014
Priority date	Feb 14, 2013
Publication date	Feb 7, 2017
Grant date	Feb 7, 2017

Abstract

A system for controlling a magnitude of a sonic boom includes a first sensor configured to detect a first condition of the supersonic aircraft. The system further includes a pair of wings configured to move fore and aft. The system further includes a processor communicatively coupled with the sensor and operatively coupled with the pair of wings. The processor is configured to (1) receive a first information from the first sensor indicative of the first condition, (2) calculate a lift distribution of the supersonic aircraft based on the first information, (3) determine an existence of a deviation of the lift distribution from a desired lift distribution based on the flight condition, and (4) control the pair of wings to move to redistribute the lift in a manner that more closely conforms to the desired lift distribution. The magnitude of the sonic boom is reduced when the deviation is reduced.

First claim

What is claimed is:

1. A system for controlling a magnitude of a sonic boom of a supersonic aircraft at supersonic speeds, the system comprising:
a first sensor configured to detect a first condition of the supersonic aircraft;
a pair of wings configured to move; and
a processor communicatively coupled with the sensor and operatively coupled with the pair of wings, the processor configured to:
receive a first information from the first sensor, the first information indicative of the first condition of the supersonic aircraft,
calculate a lift distribution of the supersonic aircraft based, at least in part, on the first information,
determine an existence of a deviation of the lift distribution from a desired lift distribution based on the flight condition,
calculate an amount and a direction of movement for the pair of wings that will reduce the deviation in response to determining the existence of the deviation, and
control the pair of wings to move the amount and the direction of movement.

2. The system of claim 1 , wherein the first sensor is configured to detect a velocity of the supersonic aircraft.

3. The system of claim 2 , wherein the processor is configured to control the pair of wings to move forward or aft based on a deviation of either (1) a Mach number of the supersonic aircraft or (2) an equivalent airspeed of the supersonic aircraft from (1) a design-condition Mach number of the supersonic aircraft or (2) a design-condition equivalent airspeed of the supersonic aircraft, respectively.

4. The system of claim 1 , wherein the first sensor is configured to detect a weight of the supersonic aircraft.

5. The system of claim 4 , wherein the first sensor is configured to determine the amount of fuel onboard the supersonic aircraft.

6. The system of claim 4 , wherein the processor is configured to control the pair of wings to move forward or aft based on a deviation of a weight of the supersonic aircraft from a design-condition weight of the supersonic aircraft.

7. The system of claim 1 , further comprising a second sensor configured to detect a second condition of the supersonic aircraft, wherein the processor is communicatively coupled to second sensor and is configured to:
receive a second information from the second sensor indicative of the second condition, and
calculate lift distribution based, at least in part, on the second information.

8. The system of claim 7 , wherein the first sensor is configured to detect a velocity of the supersonic aircraft and the second sensor is configured to detect a weight of the supersonic aircraft.

9. The system of claim 1 , wherein the processor is configured to repeatedly receive the first information from the first sensor, calculate the lift distribution, determine the existence of the deviation, and control the pair of wings to move throughout a supersonic portion of a flight of the supersonic aircraft.

10. The system of claim 9 , wherein the processor is configured to repeatedly receive the first information from the first sensor, calculate the lift distribution, determine the existence of the deviation, and control the pair of wings to move substantially continuously throughout the supersonic portion of the flight of the supersonic aircraft.

11. A method for controlling a magnitude of a sonic boom operation of a supersonic aircraft at supersonic speeds, the supersonic aircraft having a pair of wings configured to move, the method comprising the steps of:
sensing a first condition of the supersonic aircraft;
receiving, at a processor, a first information indicative of the first condition;
calculating, with the processor, a lift distribution of the supersonic aircraft based, at least in part, on the first information;
determining, with the processor, an existence of a deviation of the lift distribution from a desired lift distribution;
calculating, with the processor, an amount and a direction of movement for the pair of wings that will reduce the deviation when the existence of the deviation has been determined;
controlling, with the processor, the pair of wings to move the amount and the direction of movement.

12. The method of claim 11 , wherein the sensing step comprises sensing a velocity of the supersonic aircraft.

13. The system of claim 12 , wherein the processor is configured to control the pair of wings to move forward or aft based on a deviation of either (1) a Mach number of the supersonic aircraft or (2) an equivalent airspeed of the supersonic aircraft from (1) a design-condition Mach number of the supersonic aircraft or (2) a design-condition equivalent airspeed of the supersonic aircraft, respectively.

14. The method of claim 11 , wherein the sensing step comprises sensing a weight of the supersonic aircraft.

15. The method of claim 14 , wherein the sensing step comprise sensing an amount of fuel onboard the supersonic aircraft.

16. The system of claim 14 , wherein the processor is configured to control the pair of wings to move forward or aft based on a deviation of a weight of the supersonic aircraft from a design-condition weight of the supersonic aircraft.

17. The method of claim 11 , further comprising:
sensing a second condition of the aircraft;
receiving, at the processor, a second information indicative of the second condition; and
calculating the position of the center of pressure based, at least in part, on the second information.

18. The method of claim 17 , wherein sensing the first condition comprises sensing a velocity of the supersonic aircraft, and wherein sensing the second condition comprises sensing a weight of the supersonic aircraft.

19. The method of claim 11 , wherein the sensing step, the receiving step, the calculating step, the determining step, and the controlling step are repeated throughout a supersonic portion of a flight of the supersonic aircraft.

20. The method of claim 19 , wherein the sensing step, the receiving step, the calculating step, the determining step, and the controlling step are repeated substantially continuously throughout a supersonic portion of a flight of the supersonic aircraft.

Assignees

• Gulfstream Aerospace Corp

Inventors

• Freund Donald

Classifications

• B64C3/185

  Spars · CPC title

• B64C17/10

  Transferring fuel to adjust trim · CPC title

• B64C3/20

  Integral or sandwich constructions · CPC title

• B64C3/38

  Adjustment of complete wings or parts thereof · CPC title

• B64D37/00

  Arrangements in connection with fuel supply for power plant (refuelling during flight B64D39/00) · CPC title