Sampling-based system identification estimates physically meaningful parameters by tuning a simulator to reproduce the target system dynamics, providing an interpretable approach to improving sim-to-real transfer. Yet when the collected trajectories do not distinguish the effects of different parameters, multiple parameter combinations can reproduce those trajectories, leading to unreliable parameter estimates. To address this challenge, we introduce an Informationally Decoupled Trajectory Design framework (IDTD), which formulates the objective for the exploration policy built on the Schur complement score derived from the Fisher information matrix. To faithfully reflect parameter separability in the exploration objective, IDTD normalizes the score against the per-parameter information, selects the most favorable trajectory segment for each parameter, and aggregates the resulting scores logarithmically. The optimized trajectory is therefore composed of complementary intervals, each exposing a distinct subset of parameters whose contribution to the motion over that interval can be attributed unambiguously. Across diverse simulation environments, ranging from a linear-dynamics system to the Go2 quadruped, G1 humanoid, and Crazyflie quadrotor, IDTD reduces the parameter identification error by 39.6% on average relative to the strongest prior active-exploration baseline and attains improved downstream policy transfer. Furthermore, we validate the proposed trajectory design on a real K1 humanoid, demonstrating that the resulting identified parameters accurately capture the real-system dynamics.
Figures & tables
Fig. 1: Overview of IDTD . (1) A command sequence is rolled out in simulation over M segments. (2) Each segment yields a Fisher information F(s) , from which the per-parameter decoupling factor di(F(s);αi) follows through the Schur complement and the normalization of Sec. IV-B . (3) Each parameter takes the score ci of its best segment, and IDTD optimizes the logarithmic sum of these scores.
Fig. 2: Trajectory matching loss and parameter estimation error over CMA-ES iterations. Shaded regions indicate 95% confidence intervals.
Fig. 3: (a) Overall identification error on each platform. (b) Error ratio of each baseline to IDTD , where values above the dotted line indicate higher error than IDTD . Shaded bands show 95% confidence intervals.
Fig. 4: Forward-dynamics prediction error versus rollout horizon on the Go2. Shaded bands show 95% confidence intervals.
Method
Lin. (m/s)
Ang. (rad/s)
Fall (%)
Energy (J/m)
IDTD
0.159±.001
0.177±.002
0.71±0.26
242.8±2.7
SPI-Active
0.186±.002
0.187±.002
1.81±0.41
255.4±2.7
Passive
0.190±.002
0.234±.003
2.59±0.49
270.2±3.1
Zero-shot
0.364±.004
0.433±.006
22.35±1.26
547.9±7.4
TABLE II: Downstream transfer performance on the Go2. Mean ± 95% confidence interval, darker = higher rank.
Fig. 5: Left: covariance ellipse for the (kp,kd) pair of the wrist-pitch joint. Right: 1−∣ρij∣ for the (kp,kd) pair of all G1 joints.
Fig. 6: Left: the excitation of each kinematic channel relative to SPI-Active on a log2 scale. Right: the per-group mean of the decoupling factor di .
Group
IDTD
Mean agg.
Unidelta
α=0
kp
5.23±0.7
8.18±1.0
7.39±0.4
16.30±0.9
kd
6.71±0.7
11.72±1.5
9.05±0.7
14.85±1.8
Joint
10.99±1.4
19.63±1.5
11.03±0.7
51.41±2.7
Foot
5.90±0.9
7.31±1.0
4.29±0.5
15.09±0.8
Base
7.71±1.3
5.51±2.3
9.81±1.2
15.77±1.9
All
7.31±0.6
10.47±0.9
8.31±0.4
22.68±0.9
TABLE III: Ablation of IDTD design choices on the Go2 (50D). Mean ± 95% confidence interval, darker = higher rank.
Method
Cost
q (deg)
q˙ (rad/s)
ω (rad/s)
Orient. (deg)
Nominal
2.291
1.146
0.519
0.322
1.247
Passive
2.018±.003
1.095±.001
0.482±.001
0.314±.001
1.242±.004
SPI-Active
2.061±.005
1.108±.004
0.489±.001
0.312±.001
1.252±.003
IDTD
1.961±.005
1.074±.002
0.473±.001
0.314±.001
1.233±.005
TABLE IV: Open-loop prediction on real-world K1 trajectories. Mean ± 95% confidence interval; darker = higher rank.
Appendix figures & tables4 assets
Supplementary material from the paper’s appendix.
Appendix
Setting
Go2
G1
Crazyflie
SysID dimension P
50
68
17
Command dimension C
9
3
2
CMA-ES population
20
12
20
Maximum generations
3000
3000
3000
Initial σ0
0.25
0.25
0.25
Segments M
5
5
5
Appendix
TABLE V: Trajectory-optimization settings used in the simulation experiments.
Platform
Parameter group
αi
Go2
Base mass/inertial
1.00
Actuator PD
0.90
Foot friction
0.70
Contact
0.75
G1
Base inertial
0.80
kp
1.00
Appendix
TABLE VI: Decoupling exponents αi used for each parameter group.
Platform
Parameter
Dim.
Range
δθi
Go2
Base inertial
10
Nominal ± margin
0.10
kp (N m/rad)
12
[5.0,100.0]
2.00
kd (N m s/rad)
12
[0.1,10.0]
0.10
Joint friction (N m)
12
[0.0,5.0]
0.05
Foot friction
4
[0.1,2.0]
0.05
G1
Base inertial
10
Nominal ± margin
0.10
Appendix
TABLE VII: Parameter ranges and finite-difference perturbations used in simulation.
Parameter
Dim.
Range
δθi
αi
Torque lag ( 10 ms)
8
[0,15]
0.50
0.80
Dynamic gain
8
[0.1,1.0]
0.02
0.70
Joint friction
22
[0,0.8]
0.02
0.70
Armature ( 10−2 )
22
[0.05,15]
0.10
1.00
Appendix
TABLE VIII: Parameterization and optimization settings for the real Booster K1.
Eastern Institute of Technology, Ningbo, China · National University of Singapore, Singapore · Department of Aeronautical and Aviation Engineering, The Hong Kong Polytechnic University, Hong Kong +1