초록 ▼

The present invention is a system and method for easily adjusting flight characteristics of a simulated aircraft. The system allows a user to adjust commanded pitch, roll or yaw values or steady state frequency response values that are associated with an atmospheric temperature value, an atmospheric

The present invention is a system and method for easily adjusting flight characteristics of a simulated aircraft. The system allows a user to adjust commanded pitch, roll or yaw values or steady state frequency response values that are associated with an atmospheric temperature value, an atmospheric dynamic pressure value, aileron position, rudder position, and elevator position.

대표청구항 ▼

What is claimed is: 1. A method for adjusting a simulated position of a simulated aircraft based on at least one frequency response value for the simulated aircraft in a computer simulation application program, the method comprising: storing a computer simulation application program in a simulation

What is claimed is: 1. A method for adjusting a simulated position of a simulated aircraft based on at least one frequency response value for the simulated aircraft in a computer simulation application program, the method comprising: storing a computer simulation application program in a simulation system that includes a processor: coupling a user input device to the simulation system; enabling a user, via the user input device, to generate aircraft control signals for use by the computer simulation application when rendering an image of a simulated aircraft; coupling a user interface to the simulation system; storing in a memory of the simulation system at least one characteristic value of the simulation system; storing in the memory of the simulation system a table of predefined aircraft characteristics for the simulated aircraft operating in the simulated environment, the table of predefined aircraft characteristics remaining constant during operation of the computer simulation application program for the simulated aircraft, the table of predefined aircraft characteristics including frequency response values for pitch, yaw, and roll of the simulated aircraft with associated atmospheric temperature values and atmospheric dynamic pressure values; receiving an input from the user interface of the simulation system, the input including at least one of a commanded angle of attack, yaw angle, and roll rate; retrieving at least one frequency response value for pitch, yaw, and roll from the table of predefined aircraft characteristics based on the input from the user interface and the simulated environment providing atmospheric temperature, and atmospheric dynamic pressure values; and adjusting the simulated position of the simulated aircraft using equations of motion based on the retrieved at least one frequency response value for the simulated aircraft and the input received via the user interface of the simulation system. 2. A method for adjusting a simulated position of a simulated aircraft based on at least one of angle of attack, yaw angle, and roll rate for the simulated aircraft in a computer simulation application program, the method comprising: storing a computer simulation application program in a simulation system that includes a processor; coupling a user input device to the simulation system; enabling a user, via the user input device, to generate aircraft control signals for use by the computer simulation application when rendering an image of a simulated aircraft; coupling a user interface to the simulation system; storing in a memory of the simulation system at least one characteristic value of the simulation system; storing in the memory of the simulation system a table of predefined aircraft characteristics for the simulated aircraft operating in the simulated environment, the table of predefined aircraft characteristics remaining constant during operation of the computer simulation application program for the simulated aircraft, the table of predefined aircraft characteristics including commanded angle of attack, yaw angle, and roll rate values with an associated atmospheric temperature value, and atmospheric dynamic pressure value, and at least one of an aileron, rudder, and elevator position value of the simulated aircraft; receiving an input from the user interface of the simulation system, the input including at least one of a commanded angle of attack, yaw angle, and roll rate; retrieving at least one of the stored commanded angle of attack, yaw angle, and roll rate values from the table of predefined aircraft characteristics based on the input from the user interface and the simulated environment providing atmospheric temperature, and atmospheric dynamic pressure values; and adjusting the simulated position of the simulated aircraft using equations of motion based on the retrieved at least one of commanded angle of attack, yaw angle, and roll rate values for the simulated aircraft and the input received via the user interface of the simulation system. 3. A system for adjusting a simulated position of a simulated aircraft based on at least one frequency response value for the simulated aircraft in a computer simulation application program, the computer simulation application program stored in the system, the system comprising: a processor to execute the computer simulation application program; a user input device that enables a user to generate aircraft control signals for use by the computer simulation application program when rendering an image of a simulated aircraft; a user interface to store aircraft flight characteristic values in a memory of the simulation system, wherein the memory stores a table of predefined aircraft characteristics for the simulated aircraft, the table of predefined aircraft characteristics remaining constant during operation of the computer simulation application program for the simulated aircraft, the table of predefined aircraft characteristics including frequency response values for pitch, yaw, and roll with associated atmospheric temperature values and atmospheric dynamic pressure values; a receiver module for receiving an input from the user interface of the simulation system, the input including at least one of a commanded angle of attack, yaw angle, and roll rate; a module for retrieving at least one frequency response value for pitch, yaw, and roll from the table of predefined aircraft characteristics based on the input from the user interface and the simulated environment providing atmospheric temperature, and atmospheric dynamic pressure values; and a module for adjusting the simulated position of the simulated aircraft using equations of motion based on the retrieved at least one frequency response value for the simulated aircraft and the input received via the user interface of the simulation system. 4. A system for adjusting a simulated position of a simulated aircraft based on at least one of angle of attack, yaw angle, and roll rate for the simulated aircraft in a computer simulation application program, the computer simulation application program stored in the system, the system comprising: a processor to execute the computer simulation application program; a user input device that enables a user to generate aircraft control signals for use by the computer simulation application program when rendering an image of a simulated aircraft; and a user interface to store aircraft flight characteristic values in a memory of the simulation system, wherein the memory stores a table of predefined aircraft characteristics for the simulated aircraft operating in the simulated environment, the table of predefined aircraft characteristics remaining constant during operation of the computer simulation application program for the simulated aircraft, the table of predefined aircraft characteristics including commanded angle of attack, yaw angle, and roll rate values with an associated atmospheric temperature value, and atmospheric dynamic pressure value, and at least one of an aileron, rudder, and elevator position value; a receiver module for receiving an input from the user interface of the simulation system, the input including at least one of a commanded angle of attack, yaw angle, and roll rate; a module for retrieving at least one of the stored commanded angle of attack, yaw angle, and roll rate values from the table of predefined aircraft characteristics based on the input from the user interface and the simulated environment providing atmospheric temperature, and atmospheric dynamic pressure values; and a module for adjusting the simulated position of the simulated aircraft using equations of motion based on the retrieved at least one of commanded angle of attack, yaw angle, and roll rate values for the simulated aircraft and the input received via the user interface of the simulation system. 5. A computer based method for generating an image of an aircraft in a simulated environment, the method comprising: storing a computer simulation application program in a simulation system that includes a processor, the computer simulation application program for generating a simulated environment; storing two tables of predefined aircraft characteristics for the simulated aircraft operating in the simulated environment, the tables of predefined aircraft characteristics remaining constant during operation of the computer simulation application program for the simulated aircraft, a first table of predefined aircraft characteristics including frequency response values for pitch, yaw, and roll of the simulated aircraft with associated atmospheric temperature values and atmospheric dynamic pressure values; and a second table of predefined aircraft characteristics including commanded angle of attack, yaw angle, and roll rate values with an associated atmospheric temperature value, and atmospheric dynamic pressure value, and at least one of an aileron, rudder, and elevator position value of the simulated aircraft; entering at least one of aileron, rudder, and elevator position values for an aircraft operating in the simulated environment, the at least one of the values entered via a user input device coupled to the simulation system; providing an atmospheric temperature value and atmospheric dynamic pressure value for the aircraft; retrieving from the second table of predefined aircraft characteristics at least one of a commanded angle of attack, yaw angle, and roll rate for the aircraft based on the provided atmospheric temperature, and atmospheric dynamic pressure, and the at least provided aileron, rudder, or elevator position values; retrieving from the first table of predefined aircraft characteristics a frequency response value for at least one of pitch, roll, and yaw for the aircraft based on the provided atmospheric temperature, and atmospheric dynamic pressure; and generating an image of the aircraft based on the retrieved at least one angle of attack, yaw angle, or roll rate, frequency response value for at least one of pitch, roll, and yaw and the provided atmospheric temperature, and atmospheric dynamic pressure. 6. The method of claim 5, further comprising adjusting at least one of the frequency response values for at least one of pitch, roll, or yaw for the aircraft based on the provided atmospheric temperature, and atmospheric dynamic pressure. 7. The method of claim 5, further comprising adjusting at least one of angle of attack, yaw angle, or roll rate for the aircraft based on the provided atmospheric temperature, and atmospheric dynamic pressure, and at least one of the provided aileron, rudder, or elevator position values. 8. A computer based system for generating an image of an aircraft in a simulated environment, the system comprising: a means for storing a computer simulation application program in a simulation system that includes a processor, the computer simulation application program for generating a simulated environment; means for storing two tables of predefined aircraft characteristics for the simulated aircraft operating in the simulated environment, the tables of predefined aircraft characteristics remaining constant during operation of the computer simulation application program for the simulated aircraft, a first table of predefined aircraft characteristics including frequency response values for pitch, yaw, and roll of the simulated aircraft with associated atmospheric temperature values and atmospheric dynamic pressure values; and a second table of predefined aircraft characteristics including commanded angle of attack, yaw angle, and roll rate values with an associated atmospheric temperature value, and atmospheric dynamic pressure value, and at least one of an aileron, rudder, and elevator position value of the simulated aircraft; a means for entering at least one of aileron, rudder, and elevator position values for an aircraft operating in the simulated environment, the means being usable by a user to manipulate real-time flight characteristics of the aircraft; a means for providing an atmospheric temperature value and atmospheric dynamic pressure value for the aircraft; a means for retrieving from the second table of predefined aircraft characteristics at least one of a commanded angle of attack, yaw angle, and roll rate for the aircraft based on the provided atmospheric temperature, and atmospheric dynamic pressure, and the at least provided aileron, rudder, or elevator position values; a means for retrieving from the first table of predefined aircraft characteristics a frequency response value for the simulated aircraft for at least one of pitch, roll, and yaw for the aircraft based on the provided atmospheric temperature, and atmospheric dynamic pressure; and a means for generating an image of the aircraft based on the retrieved at least one angle of attack, yaw angle, or roll rate, the retrieved frequency response value for at least one of pitch, roll, and yaw and the provided atmospheric temperature, and atmospheric dynamic pressure. 9. The system of claim 8, further comprising a means for adjusting at least one of the frequency response values for at least one of pitch, roll, or yaw for the aircraft based on the provided atmospheric temperature, and atmospheric dynamic pressure. 10. The system of claim 8, further comprising a means for adjusting at least one of angle of attack, yaw angle, or roll rate for the aircraft based on the provided atmospheric temperature, and atmospheric dynamic pressure, and at least one of the provided aileron, rudder, or elevator position values.