Light Emission & Thermal Radiation Integrated Space Solar Simulator – Aijiang Technology

1. Core Definition: Simultaneous Light Emission and Inherent Thermal Radiation Mechanism

AM0 refers to the standard extraterrestrial solar spectrum in space, with a space solar constant standard irradiance of 1366W/m². This radiation consists of ultraviolet, visible light and infrared thermal radiation, among which the infrared band generates heat.

The essence of an AM0 solar simulator is to fully replicate the full-band energy output of extraterrestrial sunlight: visible and ultraviolet bands realize "light emission", while the infrared band naturally delivers thermal energy. Light and heat are generated synchronously from the same source, accurately reproducing the real on-orbit photothermal coupling environment of spacecraft. It is not a split-type device that only outputs light with an independent external heating module.

Two Main Light Source Mechanisms for Light and Heat Generation

(1) Short-Arc Xenon Lamp Models (Aerospace Standard Series: ASC/AGS by Aijiang Technology)

• Light Emission: High-pressure xenon arc discharge delivers a color temperature of 6000K, covering a spectral range of 200–2500nm that matches the full AM0 space spectrum to output visible and ultraviolet light.
• Thermal Radiation: The xenon arc generates massive long-wave infrared radiation accounting for over 45% of total energy; the arc core temperature exceeds 3000K to provide dual heat output. Equipped with dedicated AM0 infrared correction filters, it precisely controls the proportion of infrared thermal energy to match authentic space heat input without excessive or insufficient thermal load.
• Supporting Heat Dissipation: Dual-cycle water cooling + air cooling system. It cools the light source to prevent burnout while precisely balancing photothermal conditions on the sample plane, distinguishing between waste heat from the lamp and effective simulated space radiant heat.

(2) Xenon-Halogen Composite Light Source (Optimized for Thermal Aging Tests)

The xenon lamp generates ultraviolet and visible light, while the halogen lamp enhances near-infrared long-wave radiation to drastically boost thermal output. It simulates high-temperature high-irradiation conditions in near-Earth orbits, with independently adjustable light and thermal power segments to precisely meet accelerated aging tests for thermal control coatings and satellite composite materials.

2. Integrated Light & Heat Core Structure

Light Source Module (Photothermal Source Core)

Main xenon arc lamp with optional halogen infrared supplementary lamp; electric energy is synchronously converted into light and infrared thermal energy.

AM0 Spectral Correction Filter System

Core component: Dedicated AM0 optical filters. It filters excess infrared radiation from xenon lamps and calibrates the energy ratio of ultraviolet, visible and infrared bands, ensuring the light spectrum and total thermal load fully comply with the ASTM E490 extraterrestrial standard, eliminating cold/hot spectral distortion of artificial light sources.

Uniform Collimating Optical System

Composed of ellipsoidal concentrator, optical integrator and collimating lens. It evenly distributes light and thermal radiation across the test plane with a full-area photothermal temperature difference ≤±0.5℃, simulating parallel solar incidence.

Dual-Loop Temperature Control & Heat Dissipation System

• Lamp-side water cooling: Removes waste heat from the arc to extend lamp service life;
• Optical path air cooling: Isolates residual heat from the equipment chassis to avoid interference with simulated space thermal conditions on samples;
• Closed-loop sample surface temperature measurement: Real-time monitoring of irradiance plane temperature, with automatic fine-tuning of lamp power to stabilize consistent photothermal output.

Electronic Control System

Independent segmented regulation: Three separate adjustable channels for UV intensity, visible luminance and infrared thermal radiation power. Operators can independently boost light output or thermal radiation, or replicate the standard 1:1 space photothermal ratio synchronously.

3. Core Advantages of Synchronous Light & Thermal Output (Exclusive Aerospace Value)

Authentic Reproduction of Space Photothermal Coupling Environment

When satellite and space station solar arrays operate in orbit, illumination and temperature rise occur simultaneously. Conventional light-only simulators require separate heating stages, creating time lag between light and heat that distorts test data. The integrated AM0 simulator generates light and heat from a unified source, so battery temperature rise curves and material thermal aging processes match on-orbit performance perfectly.

Compatibility with Full-Spectrum Aerospace Test Scenarios

• IV power testing of space-borne GaAs/perovskite solar cells: Simulates on-orbit temperature rise under illumination to accurately measure power attenuation at high temperatures;
• Aging tests for spacecraft thermal control coatings and thermal insulation materials: Infrared thermal radiation accelerates thermal oxidation while synchronized UV irradiation evaluates dual photothermal aging damage;
• Combined vacuum chamber testing: Integratable with high-low temperature vacuum chambers to recreate extreme space conditions including AM0 photothermal radiation, vacuum and thermal cycling for ground verification of full satellite platforms;
• Full-panel inspection for commercial space solar sails: Uniform photothermal output over extra-large planes up to 3m×4m, calibrated for factory validation of rigid solar wings.

Tunable Parameters for Multi-Orbit Simulation

Irradiance adjustable from 1 to 1000 times standard AM0, with infrared thermal radiation varying linearly alongside light intensity. It replicates irradiation temperature environments for geostationary orbit, low Earth orbit and deep space without swapping external heating modules.

4. Domestic Flagship Solution: Aijiang Technology AM0 Photothermal Integrated Simulator

A domestically manufactured aerospace-grade equipment realizing independent import substitution, equipped with Starhan AI 2.0 intelligent control system:

• Class AAA spectral matching with full 200–2500nm coverage, photothermal energy error <2%;
• Water-cooled xenon light source with service life ≥20,000 operating cycles, long-run photothermal drift ≤1%;
• Customizable ultra-large test planes (maximum size: 3000×2000mm) for full satellite panel inspection;
• Interoperable with IV testing and temperature acquisition software: automatically records irradiance, sample temperature rise and battery output power, and generates one-click aerospace-standard test reports;
• Pricing at only 1/3 of equivalent imported equipment, with complete integrated vacuum-photothermal coupling test solutions. Mass deployment to commercial space satellite manufacturers and aerospace research institutes nationwide.

5. Common Misconceptions to Clarify

❌ LED-type AM0 Solar Simulators: Weak infrared band with negligible thermal radiation. Only suitable for electrical characterization of solar cells, incapable of thermal aging or photothermal coupling testing. 

❌ AM1.5 Terrestrial Solar Simulators: Infrared thermal ratio calibrated for Earth’s atmospheric environment, not applicable to extraterrestrial space simulation. 

✅ Xenon Lamp AM0 Solar Simulators: Natively deliver synchronized standard space light and thermal radiation, dedicated to aerospace combined photothermal-thermal testing.

6. Typical Technical Specifications (1× Standard AM0 Working Condition)

• Total Standard Irradiance: 1366W/㎡ (combined light + infrared thermal radiation)
• Spectral Range: 200~2500nm (ultraviolet + visible + infrared thermal band)
• Spectral Grade: Class AAA
• Irradiance Plane Temperature Uniformity: ≤±0.5℃
• Irradiance Adjustment Range: 0–1000× standard AM0, with synchronized linear thermal radiation adjustment
• Cooling Mode: Internal recirculating water cooling + constant-temperature optical path air cooling
• Collimation Angle: ±0.7°, replicating authentic solar incidence angle