Logo
ScienceStack
Table of Contents
Fetching ...
Sign In

Optimal Satellite Maneuvers for Spaceborne Jamming Attacks

Filippos Fotiadis, Quentin Rommel, Brian M. Sadler, Ufuk Topcu

TL;DR

The paper addresses the feasibility of spaceborne jamming against satellite uplinks by formulating a two-stage optimal-control problem in a Clohessy-Wiltshire orbital framework. It quantifies jamming impact via SINR as a function of the jammer's relative position and derives both algebraic and boundary-value solutions for repositioning and cruising phases. Simulations with a low-Earth orbit defender show that fuel-efficient maneuvers achieving small angular offsets relative to the defender can significantly degrade uplink quality, primarily through favorable antenna geometry. The work integrates communication physics, orbital mechanics, and optimal control to illuminate attack viability and motivate defensive countermeasures.

Abstract

Satellites are becoming exceedingly critical for communication, making them prime targets for cyber-physical attacks. We consider a rogue satellite in low Earth orbit that jams the uplink communication between another satellite and a ground station. To achieve maximal interference with minimal fuel consumption, the jammer carefully maneuvers itself relative to the target satellite's antenna. We cast this maneuvering objective as a two-stage optimal control problem, involving i) repositioning to an efficient jamming position before uplink communication commences; and ii) maintaining an efficient jamming position after communication has started. We obtain the optimal maneuvering trajectories for the jammer and perform simulations to show how they enable the disruption of uplink communication with reasonable fuel consumption.

Optimal Satellite Maneuvers for Spaceborne Jamming Attacks

TL;DR

The paper addresses the feasibility of spaceborne jamming against satellite uplinks by formulating a two-stage optimal-control problem in a Clohessy-Wiltshire orbital framework. It quantifies jamming impact via SINR as a function of the jammer's relative position and derives both algebraic and boundary-value solutions for repositioning and cruising phases. Simulations with a low-Earth orbit defender show that fuel-efficient maneuvers achieving small angular offsets relative to the defender can significantly degrade uplink quality, primarily through favorable antenna geometry. The work integrates communication physics, orbital mechanics, and optimal control to illuminate attack viability and motivate defensive countermeasures.

Abstract

Satellites are becoming exceedingly critical for communication, making them prime targets for cyber-physical attacks. We consider a rogue satellite in low Earth orbit that jams the uplink communication between another satellite and a ground station. To achieve maximal interference with minimal fuel consumption, the jammer carefully maneuvers itself relative to the target satellite's antenna. We cast this maneuvering objective as a two-stage optimal control problem, involving i) repositioning to an efficient jamming position before uplink communication commences; and ii) maintaining an efficient jamming position after communication has started. We obtain the optimal maneuvering trajectories for the jammer and perform simulations to show how they enable the disruption of uplink communication with reasonable fuel consumption.
Paper Structure (9 sections, 2 theorems, 16 equations, 4 figures)

This paper contains 9 sections, 2 theorems, 16 equations, 4 figures.

Table of Contents

  1. Introduction
  2. Problem Formulation
  3. Jamming Impact as a Function of Intersatellite Position
  4. Orbital Maneuvering Problem for Efficient Jamming
  5. Thrust Control for Optimal Satellite-to-Satellite Jamming
  6. Optimal Repositioning for Efficient Jamming
  7. Optimal Cruising for Efficient Jamming over a Time Window
  8. Simulation Results
  9. Conclusion

Key Result

Theorem 1

Let $u^\star\in\mathcal{U}$ be the optimal solution to eq:optT. Then: where $p_f, v_f, \mu\in\mathbb{R}^3$ solve the equations and where $W_c=\int_0^{T}e^{A\tau}BR_r^{-1}B^\mathrm{T}e^{A^\mathrm{T}\tau}\mathrm{d}\tau$ is the weighted controllability Gramian of $(A, B)$.

Figures (4)

  • Figure 1: The considered setup with the local Hill's frame centered on the defender. The ground station sends the friendly communication signal $s(t)$ to the defender, while the jammer disrupts this uplink communication with the interference signal $a(t)$.
  • Figure 2: Jammer satellite trajectory during the repositioning stage (blue) and during the jamming stage (red). The defender satellite is located at the origin of the local frame. The jammer maneuvers itself to a position from which it can view the defender's antenna. This position minimizes SINR while minimizing fuel consumption.
  • Figure 3: Communication-related trajectories generated during the maneuver.
  • Figure 4: State and control input trajectories generated during the maneuver.

Theorems & Definitions (3)

  • Theorem 1
  • Remark 1
  • Theorem 2