SIST EN 3830:2022

Aerospace series - Electrical system - Load analysis

This document defines the method to establish an electrical load analysis which is used to compare the supply capacity of an electrical power generation system with the power demand of the connected electrical utilisation equipment.
It shall prove that the power sources are capable of supplying these loads under all electrical power system states and aircraft operating conditions and that specified growth capacity for future requirements is ensured.

Luft- und Raumfahrt - Elektrisches Bordnetz - Energiebilanz

Dieses Dokument legt das Verfahren zur Erstellung einer Energiebilanz fest, in der die Leistungsfähigkeit eines Stromversorgungssystems mit den Leistungsanforderungen der angeschlossenen Verbraucher verglichen wird.
Durch die Energiebilanz ist nachzuweisen, dass die Stromquellen diese Verbraucher unter allen Betriebszu¬ständen des Stromversorgungssystems und während aller Betriebsphasen des Luftfahrzeuges versorgen können und dass die geforderte Leistungsreserve zur Abdeckung zukünftiger Anforderungen sichergestellt ist.

Série aérospatiale - Réseau électrique - Bilan électrique

Le présent document définit la méthode pour établir un bilan électrique, qui est utilisée pour comparer la capacité d'alimentation d'un réseau de production d'énergie électrique avec la demande de puissance des équipements consommateurs électriques connectés.
Il doit démontrer que les sources d'alimentation sont capables de fournir ces charges dans tous les états du réseau électrique et dans toutes les conditions de fonctionnement de l'aéronef, et que la capacité de croissance spécifiée pour les exigences futures est garantie.

Aeronavtika - Električni sistem - Analiza obremenitve

Ta dokument opredeljuje metodo za uvedbo analize električne obremenitve, ki se uporablja za primerjavo zmožnosti sistema za proizvodnjo električne energije za oskrbo z energijo in energetskih potreb povezane električne opreme.
Dokazati mora, da so viri energije zmožni zagotavljati takšne obremenitve pri vseh stopnjah elektroenergetskega sistema in v vseh obratovalnih razmerah letal ter da je zagotovljena določena zmogljivost rasti za prihodnje zahteve.

General Information

• Status: Published
• Publication Date: 17-Feb-2022
• ICS: 49.060 - Aerospace electric equipment and systems
• Technical Committee: I13 - Imaginarni 13
• Current Stage: 6060 - National Implementation/Publication (Adopted Project)
• Start Date: 16-Feb-2022
• Due Date: 23-Apr-2022
• Completion Date: 18-Feb-2022
• Ref Project: EN 3830:2022 - Aerospace series - Electrical system - Load analysis

Overview - EN 3830:2022 (Aerospace series, Electrical system - Load analysis)

EN 3830:2022 defines a method for preparing an electrical load analysis for aircraft electrical systems. The standard describes how to compare the supply capacity of electrical power generation systems (generators, TRUs, inverters, batteries, etc.) with the power demand of connected utilisation equipment across all electrical power system states and aircraft operating conditions. It ensures that power sources can supply required loads, that emergency supply requirements are met, and that growth capacity for future power needs is verified.

Key topics and technical requirements

• Scope and applicability
  • Applicable to both a.c. and d.c. aircraft electrical power systems, prepared in consideration of EN 2282 and MIL‑E‑7016F.
• Terms and definitions
  • Clear definitions for load analysis, power source analysis, busbars (main, sub, emergency, battery), primary and secondary systems, and utilisation equipment.
• Load analysis methods
  • Procedures for compiling and grouping electrical loads according to busbar arrangement.
  • Calculation of average power consumption for d.c. and a.c. loads and time‑interval handling.
• Power source analysis
  • Determination of available power, derating factors (mechanical, electromagnetic, thermal) and interval/overload ratings.
  • Overload capacity examples (e.g., 100% continuous; 150% for 5 min; 200% for 5 s).
  • Verification of power source utilisation and growth capacity.
• Battery analysis
  • Requirements for initial state of charge, charge rate determination, and remaining flight time calculations.
• Reporting
  • Structure and minimum content for the electrical load analysis report including system description, power source data and time intervals.
• Annexes
  • Informative examples (e.g., power source utilisation) and bibliographic references.

Applications and who uses EN 3830:2022

• Aerospace OEMs and system integrators - to size and validate electrical generation and distribution architectures.
• Avionics and electrical engineers - for preparing formal load analysis reports used in design reviews and certification.
• Certification authorities and safety assessors - to verify compliance with power availability and emergency requirements.
• Maintenance organizations and ground support - for understanding expected power limits, battery behavior and growth margins.
• Program managers and planners - to ensure future electrical growth capacity is quantified for system upgrades or added equipment.

Related standards

• EN 2282 - Characteristics of aircraft electrical supplies (referenced normative document).
• MIL‑E‑7016F - Considered in preparation of methods (historical reference).
• ISO/IEC terminological resources - for standardized definitions.

Keywords: EN 3830:2022, electrical load analysis, aerospace electrical system, aircraft power systems, power source analysis, AC DC load analysis, derating, battery analysis, growth capacity.

Standards Content (Sample)

SLOVENSKI STANDARD
01-april-2022
Aeronavtika - Električni sistem - Analiza obremenitve
Aerospace series - Electrical system - Load analysis
Luft- und Raumfahrt - Elektrisches Bordnetz - Energiebilanz
Série aérospatiale - Réseau électrique - Bilan électrique
Ta slovenski standard je istoveten z: EN 3830:2022
ICS:
49.060 Letalska in vesoljska Aerospace electric
električna oprema in sistemi equipment and systems
2003-01.Slovenski inštitut za standardizacijo. Razmnoževanje celote ali delov tega standarda ni dovoljeno.

EN 3830
EUROPEAN STANDARD
NORME EUROPÉENNE
February 2022
EUROPÄISCHE NORM
ICS 49.060
English Version
Aerospace series - Electrical system - Load analysis
Série aérospatiale - Réseau électrique - Bilan électrique Luft- und Raumfahrt - Elektrisches Bordnetz -
Energiebilanz
This European Standard was approved by CEN on 7 February 2020.

CEN members are bound to comply with the CEN/CENELEC Internal Regulations which stipulate the conditions for giving this
European Standard the status of a national standard without any alteration. Up-to-date lists and bibliographical references
concerning such national standards may be obtained on application to the CEN-CENELEC Management Centre or to any CEN
member.
This European Standard exists in three official versions (English, French, German). A version in any other language made by
translation under the responsibility of a CEN member into its own language and notified to the CEN-CENELEC Management
Centre has the same status as the official versions.

CEN members are the national standards bodies of Austria, Belgium, Bulgaria, Croatia, Cyprus, Czech Republic, Denmark, Estonia,
Finland, France, Germany, Greece, Hungary, Iceland, Ireland, Italy, Latvia, Lithuania, Luxembourg, Malta, Netherlands, Norway,
Poland, Portugal, Republic of North Macedonia, Romania, Serbia, Slovakia, Slovenia, Spain, Sweden, Switzerland, Turkey and
United Kingdom.
EUROPEAN COMMITTEE FOR STANDARDIZATION
COMITÉ EUROPÉEN DE NORMALISATION

EUROPÄISCHES KOMITEE FÜR NORMUNG

CEN-CENELEC Management Centre: Rue de la Science 23, B-1040 Brussels
© 2022 CEN All rights of exploitation in any form and by any means reserved Ref. No. EN 3830:2022 E
worldwide for CEN national Members.

EN 3830:2021 (E)
Contents Page
European foreword . 3
Introduction . 4
1 Scope . 5
2 Normative references . 5
3 Terms and definitions . 5
3.1 Electrical load and power analysis . 5
3.2 Electrical system . 6
3.3 Power ratings . 8
3.4 Available power . 8
3.5 Operating time . 10
3.6 Operating conditions . 10
4 Analysis report . 12
4.1 General. 12
4.2 Introduction . 12
4.3 Electrical system functional description . 12
4.4 Power sources data . 12
4.5 Time intervals . 13
5 d.c. load analysis . 13
5.1 General. 13
5.2 Minimum parameters required for the d.c. load analysis . 13
5.3 Calculation of average power consumption . 14
5.4 d.c. load summary . 14
6 a.c. load analysis . 15
6.1 General. 15
6.2 Minimum parameters required for the a.c. load analysis . 15
6.3 Calculation of average power consumption . 16
6.4 a.c. load summary . 16
7 Power source analysis . 17
7.1 General. 17
7.2 Derating . 17
7.3 Growth capacity verification . 17
7.4 Power source utilisation . 17
8 Battery analysis . 17
8.1 General. 17
8.2 Initial charge state . 18
8.3 Determination of charge rate . 18
8.4 Remaining flight time . 18
Annex A (informative) Example of power source utilisation . 19
Bibliography . 22

EN 3830:2021 (E)
European foreword
This document (EN 3830:2022) has been prepared by the Aerospace and Defence Industries
Association of Europe — Standardization (ASD-STAN).
After enquiries and votes carried out in accordance with the rules of this Association, this document has
received the approval of the National Associations and the Official Services of the member countries of
ASD-STAN, prior to its presentation to CEN.
This document shall be given the status of a national standard, either by publication of an identical text
or by endorsement, at the latest by August 2022, and conflicting national standards shall be withdrawn
at the latest by August 2022.
Attention is drawn to the possibility that some of the elements of this document may be the subject of
patent rights. CEN shall not be held responsible for identifying any or all such patent rights.
According to the CEN-CENELEC Internal Regulations, the national standards organizations of the
following countries are bound to implement this document: Austria, Belgium, Bulgaria, Croatia, Cyprus,
Czech Republic, Denmark, Estonia, Finland, France, Germany, Greece, Hungary, Iceland, Ireland, Italy,
Latvia, Lithuania, Luxembourg, Malta, Netherlands, Norway, Poland, Portugal, Republic of North
Macedonia, Romania, Serbia, Slovakia, Slovenia, Spain, Sweden, Switzerland, Turkey and the United
Kingdom.
EN 3830:2021 (E)
Introduction
This document is applicable to a.c. and d.c. aircraft electrical power systems in accordance with
EN 2282 and has been prepared under consideration of MIL-E-7016F. It describes the methods and
procedures necessary for the preparation of an electrical load analysis.
EN 3830:2021 (E)
1 Scope
This document defines the method to establish an electrical load analysis which is used to compare the
supply capacity of an electrical power generation system with the power demand of the connected
electrical utilisation equipment.
It shall prove that the power sources are capable of supplying these loads under all electrical power
system states and aircraft operating conditions and that specified growth capacity for future
requirements is ensured.
2 Normative references
The following documents are referred to in the text in such a way that some or all of their content
constitutes requirements of this document. For dated references, only the edition cited applies. For
undated references, the latest edition of the referenced document (including any amendments) applies.
EN 2282, Aerospace series — Characteristics of aircraft electrical supplies
3 Terms and definitions
For the purposes of this document, the following terms and definitions apply.
ISO and IEC maintain terminological databases for use in standardization at the following addresses:
• ISO Online browsing platform: available at https://www.iso.org/obp
• IEC Electropedia: available at https://www.electropedia.org/
3.1 Electrical load and power analysis
3.1.1
electrical load and power analysis
an electrical load and power source analysis comprises two parts:
— an analysis of the capacity of an electrical power supply system (power source analysis) ;
— an analysis of the power requirements of the utilisation equipment connected to it (load analysis)
3.1.2
power source analysis
a power source analysis determines the capacity of a power supply system to satisfy the connected
utilisation equipment under all specified aircraft conditions and provides a calculation of the
percentage load growth capacity
3.1.3
load analysis
a load analysis is essentially a compilation of the electrical loads, grouped in accordance with the
busbar arrangement of the supplying power sources, and a summation of the equipment load values
required from these during the same aircraft operating conditions as specified for the power source
analysis
EN 3830:2021 (E)
3.2 Electrical system
3.2.1
electrical system
the electrical system is an assembly constituted by the electrical power sources, utilisation equipment,
control and protection devices and all common connections of the installation
3.2.2
power supply system
a power supply system consists of one or more sources of the same nominal voltage and/or frequency,
and the corresponding power distribution system
3.2.2.1
power sources
power sources supply the power from the aircraft engines, a power conversion device, a ground power
unit or batteries
Examples of electrical power sources are:
— d.c. power sources:
• generators,
• transformer-rectifier units,
• batteries ;
— a.c. power sources:
• generators,
• transformers,
• inverters,
• frequency converters.
3.2.2.2
normal power sources
normal power sources supply electrical power to the utilisation equipment during normal system
operating conditions as defined in EN 2282
3.2.2.3
emergency power sources
emergency power sources supply electrical power to the utilisation equipment (or a specified part
thereof) in case of a failure of the normal power sources, as defined in EN 2282.
Emergency power sources may have limited (e.g. batteries) or unlimited (e.g. ram air generators)
supply duration, in general, they are limited in capacity, requiring a certain amount of load to be shed
during their operation
EN 3830:2021 (E)
3.2.3
power distribution system
a power distribution system comprises all busbars connected to one or more power sources, including
the contactors required to connect or disconnect them
3.2.3.1
busbars
a busbar is an electrical conductor used for the common supply of two or more electrical loads
connected to it. According to the intended purpose, various types of busbars may be defined, e.g.:
a) main busbar or "primary busbar"
a main busbar is used for the central distribution of power during normal operating conditions and, in
case of more than one identical power sources, may be used to connect them;
b) sub-busbar or "secondary busbar"
a sub-busbar is used to supply a defined group of electrical loads during normal operating conditions.
Depending on the function and criticality of these loads, this busbar may be classed as essential busbar,
auxiliary busbar, monitoring busbar, etc. ;
c) emergency busbar
the emergency busbar is usually supplied by the normal power source – in case of failure – by the
emergency power sources to ensure continuous supply to those loads that are vital during emergency
operation;
d) battery busbar
connected to the aircraft battery, this busbar is used to supply utilisation equipment necessary for
aircraft ground operations (e.g. canopy, obstruction lights) as well as emergency in-flight
operations (e.g. crash switch, firewall valve(s))
3.2.4
utilisation equipment
utilisation equipment is defined as any equipment or any functional group of units consuming electrical
energy
3.2.5
primary system
a primary system is characterised by one or more power sources generating electrical power from non
electric energy.
A primary power source is independent from any other electrical power source.
EXAMPLES
— generator, main-engine driven, with connected loads;
— generator, auxiliary-power unit driven with connected loads;
— battery, as an emergency power source with connected loads.
EN 3830:2021 (E)
NOTE In the case of a variable speed control frequency system being the main power source, the variable
speed control frequency components are considered as a generator.
3.2.6
secondary system
a secondary system is characterised by a power source that transforms/converts primary source power
to supply the loads connected to it. The secondary power system is entirely dependent upon the
primary system considered as a single load of the primary system, together with the connected loads.
Examples for a secondary system on an aircraft with:
— d.c. primary system: d.c./a.c. inverter with connected loads;
— a.c. primary system:
• transformer with connected loads,
• transformer-rectifier with connected loads.
3.3 Power ratings
3.3.1
nominal power ratings
the nominal power rating of an electrical device/unit of equipment, either power source or load, is its
nameplate rating which normally corresponds to continuous operation
3.3.2
power source overload capacity
the overload capacity of a power source is the potential output power, exceeding the nominal power for
short time intervals, and depends on the equipment specification, for example:
— 100 % rated power at continuous operation;
— 150 % rated power for 5 min;
— 200 % rated power for 5 s.
These figures (overload capacity and time intervals) may vary in line with the requirements specified
for the considered power source
3.3.3
power source interval rating
the interval rating of a power source is its maximum output power for a time interval defined in line
with the equipment overload capacity
3.4 Available power
3.4.1
available power
available power is the power which can be used simultaneously under steady-state conditions, taking
into account the specified conditions of use in the aircraft and the rated power of each power source
EN 3830:2021 (E)
3.4.2
derating factor
the derating factor takes into account the effects of environmental and operating conditions of the
power sources (except batteries) which normally limit the full utilisation of the rated output power. The
derating factor is the product of the corresponding individual rating factors as applicable from the
following subclauses
3.4.2.1
mechanical rating factor
the mechanical rating factor takes into account a possible reduction of the generator output power,
resulting from the mechanical drive to the power input of the generator at rated load.
The mechanical rating factor is 1, if the thermal rating factor already results in a power reduction
3.4.2.2
electromagnetic rating factor
the electromagnetic rating factor equals the ratio of maximum allowable load at operating speed to
rated load. This rating factor shall be 1, if a power supply system is already limited by the mechanical or
thermal rating factor
3.4.2.3
thermal rating factor
the thermal rating factor takes into account the effect of varying environmental and operating
conditions of the cooling medium (oil or air) and the subsequent implications on the power source
output. Utilising the specific thermal capacity of the unit, a factor of 1 may be applied for the time
interval of 5 s, as in this case the effects of temperature, altitude and pressure drop may be neglected.
For time intervals longer than 5 s appropriate figures shall be obtained from calculations and/or test
documentation.
For power supply systems already limited by the mechanical or the electromagnetic rating factor, the
thermal rating factor shall be 1
3.4.2.4
paralleling rating factor
this factor shall be applied whenever power sources are operating in parallel. For generators,
the paralleling factor shall be 0,9 unless more precise load sharing capabilities can be established
3.4.2.5
voltage drop factor
the voltage drop factor takes into account the power output limitation resulting from the voltage drop
between the generator output terminals and the related busbar. It represents the ratio between the
nominal voltage of the aircraft electrical system at the point of regulation, and the voltage measured at
the outputs terminals of the generator at rated loaf.
If the generator system is designed for nominal power at the busbar, the voltage drop factor is 1
3.4.3
derated source power
the derated source power available at the input terminals of the utilisation equipment results from the
product of the power source interval rating and the derating factor (3.4.2) com
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