Lenticular airship and associated controls

Abstract

A system for controlling yaw associated with an airship may include one or more vertical control surfaces associated with the airship, a first power source and a second power source, each configured to provide a thrust associated with the airship, and a yaw control configured to receive an input indicative of a desired yaw angle. The system may further include a controller communicatively connected to the yaw control, the one or more vertical control surfaces, and the first and second power sources. The controller may be configured to receive an output signal from the yaw control corresponding to the desired yaw angle and to generate a control signal configured to modify a state associated with at least one of the one or more vertical control surfaces, the first power source, and the second power source, such that the airship substantially attains the desired yaw angle.

1 .- 25 . (canceled) 
     
     
         26 . A system for controlling a flight parameter associated with an airship, the system comprising:
 a frame;   a support structure slidably mounted to the frame and configured to provide support to an airship control and a slider output signal indicative of an offset of the support structure from a predetermined neutral position of the frame; and   a processor communicatively connected to the frame, the support structure, and the airship control, and configured to receive the slider output signal, wherein the processor is configured to generate a control signal for modifying the flight parameter based on the slider output signal.   
     
     
         27 . The system of  claim 26 , wherein the flight parameter comprises a velocity of the airship. 
     
     
         28 . The system of  claim 26 , wherein the control signal causes a modification to at least one of a propeller pitch and a power source output associated with a power source. 
     
     
         29 . The system of  claim 26 , wherein sliding of the support structure to a position rearward of the predetermined neutral position causes a generation of a reverse thrust from the power source. 
     
     
         30 . The system of  claim 29 , wherein a force associated with the reverse thrust is proportional to a distance between the position and the predetermined neutral position. 
     
     
         31 . The system of  claim 26 , wherein sliding of the support structure to a position forward of the predetermined neutral position causes a generation of a forward thrust force from the power source. 
     
     
         32 . The system of  claim 31 , wherein a force associated with the forward thrust is proportional to a distance between the position and the predetermined neutral position. 
     
     
         33 . The system of  claim 26 , wherein the airship control comprises a hand-operated joystick communicatively connected to the processor. 
     
     
         34 . The system of  claim 33 , wherein the joystick is configured to provide a second output to the processor, independent of the slider output signal. 
     
     
         35 . The system of  claim 34 , wherein the processor is configured to receive the second output. 
     
     
         36 . The system of  claim 35 , wherein the processor is further configured to provide a second control signal for modifying a second flight parameter. 
     
     
         37 . The system of  claim 36 , wherein the second flight parameter comprises at least one of a pitch parameter associated with the airship and a roll parameter associated with the airship. 
     
     
         38 . The system of  claim 37 , wherein the second control signal is configured to modify at least one of a vertical control surface associated with the airship and a horizontal control surface associated with the airship. 
     
     
         39 . The system of  claim 26 , wherein the support structure and frame are located in a gondola associated with the airship such that the support structure functions as an arm rest for an operator of the airship. 
     
     
         40 . A method for controlling at least one parameter associated with an airship, the method comprising:
 sliding a support structure upon a frame, the support structure being configured to provide a slider output signal indicative of an offset of the support structure from a predetermined neutral position;   receiving the slider output signal at a controller; and   generating a control signal based on the slider output signal; and   modifying a flight parameter associated with the airship via the control signal.   
     
     
         41 . The method of  claim 40 , wherein the flight parameter comprises a velocity associated with the airship. 
     
     
         42 . The method of  claim 41 , wherein modifying a flight parameter comprises modifying at least one of a propeller pitch and a power source output associated with a power source. 
     
     
         43 . The method of  claim 42 , wherein the sliding of a support structure comprises sliding the support structure to a position rearward of the predetermined neutral position and causing a generation of a reverse thrust from the power source, 
     
     
         44 . The method of  claim 43 , wherein a force associated with the reverse thrust is proportional to a distance between the position and the predetermined neutral position. 
     
     
         45 . The method of  claim 42 , wherein tile sliding of the support structure comprises sliding the support structure to a position forward of the predetermined neutral position and causing a generation of a forward thrust force from the power source. 
     
     
         46 . The method of  claim 45 , wherein a force associated with the forward thrust is proportional to a distance between the position and the predetermined neutral position. 
     
     
         47 . The method of  claim 40 , wherein the support structure comprises a control comprising a hand operated joystick control, and sliding the support structure comprises sliding the control. 
     
     
         48 . The method of  claim 47 , further comprising:
 providing a second output to the processor, independent of the slider output signal;   generating a second control signal, based on the second output; and   modifying a second flight parameter based on the second control.   
     
     
         49 . The method of  claim 48 , wherein modifying the second flight parameter comprises modifying at least one of a pitch parameter associated with the airship and a roll parameter associated with the airship. 
     
     
         50 . The method of  claim 49 , wherein modifying a second flight parameter comprises modifying at least one of a vertical control surface associated with the airship and a horizontal control surface associated with the airship. 
     
     
         51 .- 100 . (canceled)