keplerian-core/dist/physics/maneuvers.d.ts

High-performance TypeScript library for orbital mechanics calculations, providing numerical integration, state propagation, and perturbation modeling for Keplerian orbits.

import { OrbitalState } from 'packages/keplerian-core/src/types/physics';
import { Vector2D } from 'packages/Keplerian-core/src/types/math';
/**
 * Applies an impulsive burn (delta-v) to the orbital state.
 * This instantaneously changes the velocity vector of the spacecraft.
 * @param state The current orbital state.
 * @param deltaV The change in velocity vector to apply.
 * @returns The new orbital state after the burn.
 */
export declare function applyImpulsiveBurn(state: OrbitalState, deltaV: Vector2D): OrbitalState;
/**
 * Calculates the acceleration due to continuous thrust.
 * This is a simplified 2D model where thrust is applied in a specific direction.
 * @param thrustMagnitude The magnitude of the thrust force.
 * @param spacecraftMass The mass of the spacecraft.
 * @param thrustDirection The normalized direction vector of the thrust.
 * @returns The acceleration vector due to thrust.
 */
export declare function calculateThrustAcceleration(thrustMagnitude: number, spacecraftMass: number, thrustDirection: Vector2D): Vector2D;
/**
 * Placeholder for modeling continuous thrust over a duration.
 * This would typically involve integrating the thrust acceleration over time
 * within the simulation loop.
 * @param state The current orbital state.
 * @param thrustMagnitude The magnitude of the thrust force.
 * @param spacecraftMass The mass of the spacecraft.
 * @param thrustDirection The normalized direction vector of the thrust.
 * @param deltaTime The time step over which thrust is applied.
 * @returns The new orbital state after applying continuous thrust for deltaTime.
 */
export declare function applyContinuousThrust(state: OrbitalState, thrustMagnitude: number, spacecraftMass: number, thrustDirection: Vector2D, deltaTime: number): OrbitalState;