litzj

what is announced loadout?

Can dev.team provide roadmap of F1's weapons set? I am curious about which guided munition will be added?

what would be the weapon loadout of mirage f1m?

I hope enjoy this

I found I released bomb too early! That would be work if I release properly. Thanks Swordman

Is there anyone testing lantirn pod w/ LGB after this patch? I just tested only once but GBU-10 did not follow lasing (though it can be my mistake)

https://jaesan-aero.blogspot.com/2019/09/missile-sim-performance-evaluation-for_14.html Test for ATACMS missile class

https://jaesan-aero.blogspot.com/2019/05/aim-120c-study-using-missile-sim-part-3.html Before I expand my simulation, there is few additional result for AIM-120 related stuff

https://jaesan-aero.blogspot.com/2019/04/aim-120c-study-using-missile-sim-part-3.html I did sensitivity analysis for the previous missiles

https://jaesan-aero.blogspot.com/2019/03/aim-120c-study-using-missile-sim-part-3.html I have compared generic model of CUDA / AIM-120C / CUDA+Booster / Meteor class missiles

Nice attempt !!

https://jaesan-aero.blogspot.com/2019/02/wip-status-of-missile-sim-addition-of.html I have added Ramjet style option for the Missile-SIM, and tested for the generic Ramjet AtA missile. ISP of missile is changed by flight condition (AoA, M)

https://jaesan-aero.blogspot.com/2019/01/wip-status-of-missile-sim-addition-of.html I am working on ISP part update for air-breathing engine of the missiles. Also, I had tested some inlet CFD for DB construction.

Ya, I hope there will be a good tool for performance test of missiles

Estimation for the rocket motor performance cannot be exact because exact burning profile or ISP is in secret. Also, my CFD also has limitation in accuracy because of limited computing source. Now I am currently working for addition of air-breathing propulsion for my Missile-SIM, like ramjet and scramjet.

Original model is B model, YES, but I cut the edge of the tail fins to fit C model. Unfortunately, parameters of the missiles were estimated from another reference; exact value of rocket motor is basically classified. Still, the simulation is under the development status; some functions providing different thrust for the given stage is configured while optimized control functions are WIP Thanks for your interest. I will update my SIM result when the new feature is available

https://jaesan-aero.blogspot.com/2018/11/patch-note-of-missile-sim-guidance.html There is real-time plot video for the Missile-SIM (Guidance of Missile with 0.1s time step)

I just published update of AIM-120C study using Missile-SIM https://jaesan-aero.blogspot.com/2018/10/aim-120c-study-using-missile-sim-part-2.html

Full detail of the Article is here. https://jaesan-aero.blogspot.com/2018/10/aim-120c-study-using-missile-sim-part-1.html As the first study object, AIM-120C is chosen, and the objective of the study is sensitivity analysis for range performance and its optimization. Range of study includes "Rocket parameter", "Launch condition", and "Multi-stage version of CUDA". This Part 1 will show sensitivity analysis of rocket parameter for AIM-120C baseline missile; Part 2 is optimization of rocket parameters and launch condition for longer range; Part 3 is proposal of AIM-120 sized dual-stage CUDA missile with optimized configuration. Part 1 : Sensitivity Analysis of AIM-120C As shown in Fig. 1-1, baseline of AIM-120C is modeled; some part of the data like propellant weight, and burn time are referenced from previous estimation work. Target parameters of the sensitivity are propellant weight, burn-time, ISP, Drag(CD), Lift(CL), and usage of dual-pulse. Reference launch condition is set as M1.3 at 30000ft, and I assumed missile go straight without altitude change. Range is calculated when speed of the missile is re-decreased as M1.3 (The missile should pursue target having at least M1.3 speed). As a summary of Sensitivity (M1.3, 30kft) (1) 1.2 km Range↑, M 0.1 Speed↑ via 1.0 kg↑of Propellant (in given total weight) (2) 0.67 km Range↑, almost zero Speed change via 1.0 s↑of Burn time (smaller mass-flow) (3) 0.2 km Range↑, M 0.01 Speed↑ via 1.0 s↑of ISP (4) 0.65 km Range↑, almost zero Speed change via 1.0 % Drag reduction (5) almost zero Range, almost zero Speed change via 1.0 % Lift↑(negligible) (6) 0.4 km Range↑, M 0.02 Speed↓ via 1.0 s increase of Dual pulse interval Change of Lift is almost negligible for both range and peak speed performance. Higher lift configuration having more, longer, or larger fins is related to maneuverability and stability. It is natural that increase of some parameters (Propellant, and ISP) are directly proportional to the range and speed increase. Longer Burn-time and Drag reduction can increase range without change of speed performance. (Tendency can be changed at different reference condition) It could be interesting result that increase of Pulse interval can extend range while small decrease of peak speed. In given hardware specification (weight, propellant, ISP, lift, and drag), longer burn-time and pulse interval are recommended to extend the range of the AIM-120C class missile. Improvement via optimization will be performed at Part 2; Result of this sensitivity is applied while study for trajectory and launch condition will be conducted

https://jaesan-aero.blogspot.com/2018/09/aerodynamic-validation-of-missile-sim.html Recent update : validation for CFD setting for generic missile shape. Unfortunately, I cannot achieve very precise aerodynamic coefficient due to limitation of CFD computing source

http://jaesan-aero.blogspot.com/2018/09/initial-version-of-missile-sim-for.html I planned to make performance evaluation of the missile for its range. Coefficient of missile should be calculated by CFD (M, AoA)