Devices and method for rocket booster vectoring to provide stability augmentation during a booster launch phase

• US 4,721,271 A
• Filed: 02/14/1985
• Issued: 01/26/1988
• Est. Priority Date: 02/14/1985
• Status: Expired due to Fees

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Pera, Ronald J., Goldstein, Sidney E.
• Primary Examiner(s): BAREFOOT, GALEN L
• Application Number:
  US06/701,381
• Time in Patent Office: 1,076 Days
• Field of Search: 244/52, 244/58, 244/76 A, 244/160, 244/50, 244/51, 244/56, 244/63, 244/74, 244/2, 244/3.22, 244/54, 244/75 R
• US Class Current: 244/75.1
• CPC Class Codes: B64C 15/14 the jets being other than main propulsion jets jet flaps B64C9/38

Abstract

Rocket booster motor vectoring system and method for shortening take-off distance of aircraft, the aircraft being airborne before it is going fast enough for its conventional controls to provide adequate stability and control. A rocket booster motor (52) is coupled to aircraft (50) by means of thrust arm link (56) is pivotal engagement with the aircraft and fixed to the booster, and coupled by rearwardly positioned links (62, 64, 66) having ball and socket joints at both ends, one end being connected to the aircraft through aerodynamic surfaces (68, 70) or through actuators (124, 126), the aerodynamic surfaces being operable by conventional systems within the basic aircraft, and the actuators also being operated by motion sensing systems within the aircraft to vector the thrust of the booster to provide stability augmentation of the aircraft during the boosted launch phase to provide pitch, roll, and yaw control. The thrust vector is rotated or directed in response to signals generated in the basic aircraft control systems.

Claims

1. For use in aircraft having motion sensors and required logic coupled to aerodynamic controls, such as elevons, ailerons, elevators, and rudder, for augmenting stability in the post launch phases of climb, high speed flight, and landing;

a rocket booster motor for coupling to at least some of said controls so that the rocket booster thrust vector is directed in response to signals generated to the controls in the basic aircraft to provide additional stability and control required during a boosted launch phase, with no changes in the flight control logic or system, the invention comprising;

means for coupling a rocket booster motor to at least some of said controls so that when said coupled controls are operated in accordance with said signals from said motion sensors and/or logic to the controls, the rocket thrust vector is directed relative to the center of gravity of the aircraft to prevent generation of excessive torques, to avoid placing additional demands on the controls, to avoid severely limiting of available aerodynamic control at low launch speeds, and to provide pitch, roll, and yaw control,

wherein said means for coupling are supporting links;

a forward link of said links having a forward end for pivotal connection to the aircraft aft of its center of gravity and having a rearward end fixed to the rocket motor;

a first rear link having ball joints at both ends, one of said ends of said first rear link being connectable to a control on one side of the aircraft;

the other end of said first rear link being connected to a corresponding one side of said rocket motor;

second and third rear links having ball joints at both ends, one of aid ends of each of said second and third rear links being connectable to a control on the other side of said aircraft;

the other ends of said second and third rear links being spacedly connected to a corresponding other side of said rocket motor.

2. The invention according to claim 1 in which:

said controls are elevons.

3. The invention according to claim 2 in which:

said forward link is positioned to be aligned with the direction of the rocket thrust.

4. For use in aricraft having motion sensors and required logic coupled to aerodynamic controls, such as elevons, ailerons, elevators, and rudder, for augmenting stability in the post launch phases of climb, high speed flight, and landing:

a rocket booster motor for coupling to at least some of said controls so that the rocket booster thrust vector is directed in response to signals generated to the controls in the basic aircraft to provide additional stability and control required during a boosted launch phase, with no changes in the flight control logic or system, the invention comprising;

means for coupling a rocket booster motor to at least some of said controls so that when said coupled controls are operated in accordance with said signals from said motion sensors and/or logic to the controls, the rocket thrust vector is directed relative to the center of gravity of the aircraft to prevent generation of excessive torques, to avoid placing additional demands on the controls, to avoid severely limiting of available aerodynamic control at low launch speeds, and to provide pitch, roll, and yaw control,

wherein said means for coupling include supporting links;

a forward link of said links having a forward end for ball joing connection to the aircraft aft of its center of gravity and having a rear end fixed to the rocket motor;

a first rear link having pivotal joints at both ends and being connectable at one end to a control on one side of th aircraft and one side of the rocket motor;

a second rear link having pivotal joints at both ends and being connectable at one end to a control on the other side of the aircraft and the other side of the rocket motor;

a transverse link having one end connected to the other end of said first rear ink and having its other end connected to the other end of said second rear link, said links being joined in pivotal connections;

a pivot sleeve connected to said rocket motor and through which said transverse link is slidably and rotatably engaged; and

a roll and yaw actuator having its operable shaft having its outer end joined to the rocket motor in a ball and socket connection, the operation of the shaft by th actuator being to move the motor transversely with respect to the aircraft;

said actuator being joined to one of said rar links at its other end and to a corresponding end of said transverse link in a pivotal connection, said actuator being connectable to receive signals generated in the basic aircraft for operation.

5. The invention according to claim 4 in which:

said controls are elevators.

6. The invention according to claim 5 in which:

said forward link is positioned to be aligned with the direction of the rocket thrust.

7. For use in aircraft for providing additional stability and control required during a booster launch phase, a rocket booster motor for coupling to the aircraft so that the rocket booster thrust vector is directed in response to controls in the basic aircraft, with no changes in the flight control or logic system, the invention comprising:

means for coupling a rocket booster motor to the aircrat to respond to controls in the aircraft so that the rocket thrust vector is directed relative to the center of gravity of the aircraft to maintain stability of the aircraft, to prevent generation of excessive torques, to avoid placing additional demands on the aircraft structure, to avoid severely limiting of available aerodynamic control at low launch speeds, and to provide pitch, roll, and yaw control;

said means for coupling including a forward link having a spherical roller on its forward end for rollable contact on a concave spherical member securable to the aircraft and having a rearward end fixed to the rocket motor;

a first rear link having ball joints at both ends, one of said ends of said first rear link being connectable to the aircraft;

the other end of said first rear link being connected to the rocket motor;

a second rear link having ball joints at both ends, one of said ends of said first rear link being connectable to the aircrat;

the other end of said second rear link being connected to the rocket motor; and

a pair of actuators having one end of each joining said forward link between the spherical roller and its fixed end;

said actuators being angularly positioned so that their other ends are spaced and are connectable to the aircraft;

whereby a forward thrust point in the spherical roller is movable on the concave spherical member by the actuators to provide pitch, roll, and yaw control to the aircraft through the thrust vector of the rocket motor.

8. The invention according to claim 7 in which:

said forward link is positioned to be aligned with the direction of the rocket thrust.

9. An aircraft having a rocket booster motor coupled thereto for providing additional stability and control required during a booster launch phase so that the rocket booster thrust is directed in response to controls in the basic aircraft, comprising:

means coupling a rocket booster motor to the aircraft to respond to flight controls in the aircraft so that the rocket thrust vector is directed relative to the center of gravity of the aircraft to maintain stability of the aircraft, to prevent generation of excessive torques, to avoid placing additional demands on the aircraft structure, to avoid severely limiting of available aerodynamic control at low launch speeds, and to provide pitch, roll, and yaw control;

said means for coupling include a forward link having a spherical roller on its forward end for rollable contact on a concave spherical member secured to the aircraft and having a rearward end fixed to the rocket motor;

a first rear link having ball joints at both ends, one of said ends of said first rear link being connected to the aircraft;

the other end of said first rear link being connected to the rocket motor;

a second rear link having ball joints at both ends, one of said ends of said second rear link being connected to the aircraft;

the other end of said second rear link being connected to the rocket motor;

a pair of actuators having one end of each joining said forward link between the spherical roller and its fixed end; and

said actuators being angularly positioned so that their other ends are spaced and connected to the aircraft;

whereby a forward thrust point in the spherical roller is movable on the concave spherical member by the actuators to provide pitch, roll, and yaw control to the aircraft through the thrust vector of the rocket motor.

10. The invention according to claim 9 in which:

said forward link is positioned in alignment with the direction of the rockt thrust.

11. An aircraft having a rocket booster motor coupled thereto for providing additional stability and control required during a booster launch phase so that the rocket booster thrust is directed in response to controls in the basic aircraft, comprising:

means coupling a rocket booster motor to the aircraft to respond to flight controls in the aircraft so that the rocket thrust vector is directed relative to the center of gravity of the aircraft to maintain stability of the aircraft, to prevent generation of excessive torques, to avoid placing additional demands on the aircraft structure, to avoid severely limiting of available aerodynamic control at low launch speeds, and to provide pitch, roll, and yaw control;

the aircraft having aerodynamic control surfaces for coupling to controls in the aircraft for augmenting stability in the post launch phases of climb, speed flight, and landing;

said means for coupling being supporting links;

a forward link of said links having a forward end pivotally connected to the aircraft aft of its center of gravity and having a rearward end fixed to the rocket motor;

a first rear link having ball joints at both ends, one of said ends of said first rear link being connected to an aerodynamic control surface on one side of the aircraft;

the other end of said first rear link being connected to a corresponding one side of said rocket motor;

second and third rear links having ball joints at both ends, one of said ends of each of said second and third rear links being connected to an aerodynamic control surface on the other side of the aircraft;

the other ends of said second and third rear links being spacedly connected to a corresponding other side of said rocket motor.

12. The invention according to claim 11 in which:

said aerodynamic controls are elevons.

13. The invention according to claim 12 in which:

said forward link is aligned with the direction of the rocket thrust.

14. An aircraft having a rocket booster motor coupled thereto for providing additional stability and control required during a booster launch phase so that the rocket booster thrust is directed in response to controls in the basic aircraft, comprising:

means coupling a rocket booster motor to the aircraft to respond to flight controls in the aircraft so that the rocket thrust vector is directed relative to the center of gravity of the aircraft to maintain stability of the aircraft, to prevent generation of excessive torques, to avoid placing additional demands on the aircraft structure, to avoid severely limiting of available aerodynamic control at low launch speeds, and to provide pitch, roll, and yaw control;

the aircraft having aerodynamic control surfaces for coupling to controls in the aircraft for augmenting stability in the post launch phases of climb, speed flight, and landing;

said means for coupling including supporting links;

a forward link of said links having a forward end ball joint connected to the aircraft aft of its center of gravity and having a rear end fixed to the rocket motor;

a first rear link having pivotal joints at both ends and being connected at one end to an aerodynamic control surface on one side of the aircraft and on one side of the rocket motor;

a second rear link having pivotal joints at both ends and being connected at one end to an aerodynamic control surface on the other side of the aircraft and the other side of the rocket motor;

a transverse link having one end connected to the other end of said first rear link and having its other end connected to the other end of said second rear link, said links being joined in pivotal connections;

a pivot sleeve connected to said rocket motor and through which said transverse link is slidably and rotatably engaged; and

a roll and yaw actuator having its operable shaft having its outer end joined to the rocket motor in a ball and socket connection, the operation of the shaft by the actuator being to move the motor transversely with respect to the aircraft;

said actuator being joined to one of said rear links at its other end and to a corresponding end of said transverse link in a ball and socket connection, and being operated by the flight controls.

15. The invention according to claim 14 in which:

said aerodynamic control surfaces are on elevators.

16. The invention according to claim 15 in which:

said forward link is in alignment with the direction of the rocket thrust.

17. A method of providing additional stability and control to aircraft during a booster launch phase when a booster is used to shorten takeoff distance and the aircraft files before it is going fast enough for its conventional controls to provide adequate stability and control, comprising:

coupling a rocket booster motor to the aircraft so that the rocket booster thrust vector is directed in response to controls in the basic aircraft; and

directing the rocket thrust vector relative to the center of gravity of the aircraft to maintain stability of the aircraft, to prevent generation of excessive torques, to avoid placing additional demands on the aircraft structure, to avoid severely limiting of available aerodynamic control at low launch speeds, and to provide pitch, roll, and yaw control;

said rocket booster motor is coupled to an aircraft by;

a forward link having a spherical roller on its forward end for rollable contact on a concave spherical member securable to the aircraft and having a rearward end fixed to the rocket motor;

a first rear link having ball joints at both ends, one of said ends of the first rear link being connectable to the aircraft;

the other end of said first rear link being connected to the rocket motor;

a second rear link having ball joints at both ends, one of said ends of the second rear link being connectable to the aircraft;

the other end of said second rear link being connected to the rocket motor; and

a pair of actuators having one end of each joining said forward link between the spherical roller and its fixed end;

said actuators being angularly positioned so that their other ends are spacedly connectable to the aircraft;

whereby a forward thrust point in the spherical roller is movable on the concave spherical member by the actuators to provide pitch, roll, and yaw control to the aircraft through the thrust vector of the rocket motor.

18. The method according to claim 17 including:

positioning the forward link to be in alignment with the direction of the rocket thrust.

19. A method of providing additional stability and control to aircraft during a booster launch phase when a booster is used to shorten takeoff distance and the aircraft flies before it is going fast enough for its conventional controls to provide adequate stability and control, comprising:

coupling a rocket booster motor to the aircraft so that the rocket booster thrust vector is directed in response to controls in the basic aircraft; and

directing the rocket thrust vector relative to the center of gravity of the aircraft to maintain stability of the aircraft, to prevent generation of excessive torques, to avoid placing additional demands on the aircraft structure, to avoid severely limiting of available aerodynamic control at low launch speeds, and to provide pitch, roll, and yaw control;

the rocket booster motor being coupled in part to aerodynamic control surfaces in the aircraft and which said control surfaces are coupled to controls in the aircraft for augmenting stability in the post-launch phases of climb, speed flight and landing;

coupling said rocket motor to the aircraft and aerodynamic control surfaces by supporting links;

a forward link of said links having a forward end pivotally connected to the aircraft aft of its center of gravity and having a rearward end fixed to the rocket motor;

a first rear link having ball joints at both ends, one of said ends of said first rear link being connected to an aerodynamic control surface on one side of the aircraft;

the other end of said first rear link being connected to a corresponding one side of said rocket motor;

second and third rear links having ball joints at both ends, one of said ends of each of said second and third rear links being connected to an aerodynamic control surface on the other side of the aircraft;

the other ends of said second and third rear links being spacedly connected to a corresponding other side of said rocket motor.

20. The method according to claim 19 in which:

said aerodynamic controls are elevons.

21. The method according to claim 20 in which:

said forward link is aligned with the direction of the rocket thrust.

22. A method of providing additional stability and control to aircraft during a booster launch phase when a booster is used to shorten take-off distance and the aircraft flies before it is going fast enough for its conventional controls to provide adequate stability and control, comprising:

coupling a rocket booster motor to the aircraft so that the rocket booster thrust vector is directed in response to controls in the basic aircraft; and

directing the rocket thrust vector relative to the center of gravity of the aircraft to maintain stability of the aircraft, to prevent generation of excessive torques, to avoid placing additional demands on the aircraft structure, to avoid severely limiting of available aerodynamic control at low launch speeds, and to provide pitch, roll, and yaw control;

the coupling of the rocket booster being in part to aerodynamic control surfaces coupled to controls in the aircraft for augmenting stability in the post-launch phases of climb, speed flight, and landing;

the rocket booster motor being coupled to the aircraft and control surfaces by supporting links;

a forward link of said links having a forward end ball joint connected to the aircraft aft of its center of gravity and having a rear end fixed to the rocket motor;

a first rear link having pivotal joints at both ends and being connected at one end to an aerodynamic control surface on one side of the aircraft and on one side of the rocket motor;

a second rear link having pivotal joints at both ends and being connected at one end to an aerodynamic control surface on the other side of the aircraft and the other side of the rocket motor;

a transverse link having one end connected to the other end of said first rear link and having its other end connected to the other end of said second rear link, said links being joined in pivotal connections;

a pivot sleeve being connected to said rocket motor and through which said transverse link is slidably and rotatably engaged; and

a roll and yaw actuator having its operable shaft having its outer end joined to the rocket motor in a ball and socket connection, the operation of the shaft by the actuator being to move the motor transversely with respect to the aircraft;

said actuator being joined to one of said links at its other end and to a corresponding end of said transverse link in a pivotal connection, and being operable by the flight controls.

23. The method according to claim 22 in which:

said aerodynamic control surfaces are on elevators.

24. The method according to claim 23 in which:

said forward link is in alignment with the direction of the rocket thrust.