Flight Parameters

Calculate aerospace parameters such as ideal airspeed correction, Mach number, dynamic pressure

Calculate common flight dynamics parameters, such as incidence, sideslip, and airspeed.

Blocks

Incidence, Sideslip, & Airspeed	Calculate incidence, sideslip, and airspeed
Dynamic Pressure	Compute dynamic pressure using velocity and air density
Ideal Airspeed Correction	Calculate equivalent airspeed (EAS), calibrated airspeed (CAS), or true airspeed (TAS) from each other
Incidence & Airspeed	Calculate incidence and airspeed
Incidence, Sideslip, & Airspeed	Calculate incidence, sideslip, and airspeed
Mach Number	Compute Mach number using velocity and speed of sound
Radius at Geocentric Latitude	Estimate radius of ellipsoid planet at geocentric latitude
Relative Ratio	Calculate relative atmospheric ratios
Wind Angular Rates	Calculate wind angular rates from body angular rates, angle of attack, sideslip angle, rate of change of angle of attack, and rate of change of sideslip

Featured Examples

Quadcopter Project

Use Simulink® to model a quadcopter, based on the Parrot® series of mini-drones. To manage the model and source files, it uses Project Management.

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Developing the Apollo Lunar Module Digital Autopilot

"Working on the design of the Lunar Module digital autopilot was the highlight of my career as an engineer. When Neil Armstrong stepped off the LM (Lunar Module) onto the moon's surface, every engineer who contributed to the Apollo program felt a sense of pride and accomplishment. We had succeeded in our goal. We had developed technology that never existed before, and through hard work and meticulous attention to detail, we had created a system that worked flawlessly." -Richard J. Gran, The Apollo 11 Moon Landing: Spacecraft Design Then and Now

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HL-20项目可选FlightGear接口

这个项目显示了如何模型美国宇航局HL-20 lifting body with Simulink®, Stateflow® and Aerospace Blockset™ software. The vehicle model includes the aerodynamics, control logic, fault management systems (FDIR), and engine controls (FADEC). It also includes effects of the environment, such as wind profiles for the landing phase. The entire model simulates approach and landing flight phases using an auto-landing controller. To analyze the effects of actuator failures and wind gust variation on the stability of the vehicle, use the "Run Failure Analysis in Parallel" project shortcut. If Parallel Computing Toolbox™ is installed, the analysis is run in parallel. If Parallel Computing Toolbox™ is not installed, the analysis is run in serial. Visualization for this model is done via an interface to FlightGear, an open source flight simulator package. If the FlightGear interface is unavailable, you can simulate the model by closing the loop using the alternative data sources provided in the Variant block. In this block, you can choose a previously saved data file, a Signal Editor block, or a set of constant values. This example requires Control System Toolbox™.

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Lightweight Airplane Design

How to use MathWorks® products to address the technical and process challenges of aircraft design using the design of a lightweight aircraft.

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Indicated Airspeed from True Airspeed Calculation

How to compute the indicated airspeed from true airspeed using the Ideal Airspeed Correction block. The Aerospace Blockset™ blocks are indicated in red.

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True Airspeed from Indicated Airspeed Calculation

How to compute true airspeed from indicated airspeed using the Ideal Airspeed Correction block. The Aerospace Blockset™ blocks are indicated in red.

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