Electric paramotors bring several battery design variables together in a very compact aircraft: onboard energy, propulsion power, battery weight, system voltage, thermal behavior, and available installation space.
At Grepow, we see a familiar engineering problem behind this application. Professional UAVs, VTOL aircraft, and other electric aviation platforms also need to carry enough energy to complete a mission without adding unnecessary battery mass. Their propulsion systems may demand much more power during takeoff and climb than during steady flight.
The difference is that a foot-launched electric paramotor places those requirements directly on a pilot-carried propulsion system.
That is why we do not start an electric paramotor battery project with one question such as, "How many kWh do you need?"
We start with the complete flight mission.
What Is Paramotoring, and Why Does Battery Weight Matter?
For readers searching "what is paramotoring," a paramotor is a powered paraglider in which a motor and propeller provide thrust beneath a paraglider wing. A foot-launched pilot normally carries the propulsion unit on the back during takeoff. Terms such as paramotor, para motor, motorized paraglider, and powered paraglider are also used in searches and product discussions.
An electric paramotor replaces the combustion engine and fuel system with an electric motor, controller, and propulsion battery.
This makes battery mass particularly important.
In the United States, the Federal Aviation Administration treats motorized paragliders that meet the applicable definition as ultralight vehicles under Part 103. The regulation includes an empty-weight limit for powered ultralights, illustrating why weight is an aircraft-level constraint rather than simply a battery specification. (Federal Aviation Administration)
More battery energy can support longer powered flight, but the additional cells also increase the mass that the aircraft must carry and, in many foot-launched designs, the weight the pilot must handle during launch.
The right battery is therefore not automatically the largest battery.
Battery Capacity Cannot Be Selected by kWh Alone
Battery energy is usually one of the first specifications discussed in an electric aircraft project. It still does not tell us whether the battery will work in the aircraft.
A flight battery has to provide both energy and power.
Research published in the Journal of Power Sources identifies the simultaneous need for high gravimetric energy density, power density, safety, reliability, and acceptable operation across different conditions as a central challenge for electric-aircraft battery design. (Journal of Power Sources)
At Grepow, we normally break an electric paramotor requirement into five basic questions:
How much energy does the mission require?
What is the maximum acceptable complete battery weight?
What peak power must the propulsion system receive?
How long must high power be maintained?
What voltage platform will the motor and controller use?
These numbers have to be evaluated together.
Two motorized paragliders can use batteries with similar nominal energy and still need very different battery designs. One may demand a short, high-power takeoff followed by relatively modest cruise power. Another may stay at substantial power for a longer climb.
The kWh figure may look similar, but cell selection, current capability, conductors, thermal behavior, BMS settings, and pack architecture can differ considerably.
What Electric Paramotors Share With UAV and eVTOL Battery Design
Electric paramotors are a different aircraft architecture, but many of their battery problems are familiar to us.
Grepow has developed battery solutions for professional UAV applications including mapping, inspection, logistics, agriculture, long-endurance aircraft, and VTOL platforms. Our UAV portfolio covers high-discharge pouch batteries, smart battery systems, high-energy-density semi-solid-state batteries, BMS integration, and charging solutions. (Grepow UAV Battery Solutions)
That experience provides a useful engineering foundation for electric paramotor development.
Where UAV and eVTOL Experience Transfers
Several requirements are common across aerial battery systems:
High energy with limited onboard mass
Peak propulsion power during demanding flight phases
Stable loaded voltage
High-current conductor and connector design
Temperature monitoring
Battery state monitoring
BMS communication
Limited installation volume
Cell and pack performance at different states of charge
Takeoff is a useful example.
Battery research for eVTOL aircraft separates high-power takeoff and landing phases from other portions of the flight because power demand can vary significantly throughout a mission. The same principle applies when sizing batteries for other electrically propelled aircraft. (Joule: Batteries for Electric Vertical Takeoff and Landing Aircraft)
So when an electric paramotor manufacturer tells us only the maximum motor power, we still need another important piece of information:
For how long?
Where Electric Paramotors Are Different
Experience does not mean the battery systems are interchangeable.
A professional UAV usually carries its propulsion battery as part of an unmanned aircraft. A foot-launched paramotor may require the pilot to carry the motor, frame, propeller, electronics, and battery during launch.
One additional kilogram can therefore affect more than flight endurance. It can also affect:
Ground handling
Launch practicality
Frame loading
Balance and mounting
Pilot-carried mass
A crewed aircraft also requires its own system-level safety assessment. BMS behavior, propulsion control, mechanical installation, fault response, warning logic, and aircraft integration need to be evaluated for that specific platform.
Our approach is therefore to transfer the battery engineering principles that already work in demanding aerial applications, then redesign and validate the parts that are specific to the paramotor.
How Much Battery Energy Does an Electric Paramotor Need?
There is no universal kWh value for every electric paramotor.
The required energy depends on the aircraft mission.
A lightweight system designed around short powered flights may favor minimum battery mass. A longer-endurance aircraft requires more stored energy and accepts a different weight trade-off.
This creates three broad design directions.
Lightweight Battery Systems
For a lightweight configuration, reducing carried mass is often more valuable than maximizing flight time.
The design may prioritize:
High cell-level specific energy
Efficient packaging
Minimal structural overhead
Enough power for launch and climb without excessive unused capacity
These systems can be relevant to shorter flights, development aircraft, launch practice, or missions where long continuous powered flight is not required.
Longer-Endurance Battery Systems
Longer powered flight requires more stored energy.
The challenge is that each additional watt-hour comes with additional battery mass.
Electric aviation research consistently identifies specific energy as an important limiting factor because the aircraft has to carry its own energy storage throughout the mission. Battery housings, thermal systems, connections, and structural components further reduce the specific energy of the finished system compared with the cells alone. (Progress in Aerospace Sciences: Energy Storage for Sustainable VTOL Aircraft)
The engineering question is therefore not:
How much battery can we install?
It is:
How much battery produces useful additional mission endurance after the additional mass is included?
Balanced Systems
Many real aircraft sit between these two extremes.
They need:
Practical flight endurance
Manageable battery weight
Sufficient takeoff power
Sustained climb capability
Acceptable thermal performance
In these projects, no single battery parameter should be maximized independently.
Complete Pack Weight Matters More Than Cell Weight
High cell energy density is valuable for an electric paramotor, but cell Wh/kg should not be confused with finished battery pack Wh/kg.
The basic cell-level calculation is:
Specific Energy = Cell Energy / Cell Mass
This is useful when comparing cell technologies.
But an aircraft does not fly with bare cells.
A complete propulsion battery may also contain:
Structural supports or compression components
Battery enclosure
Busbars
High-current cables
BMS hardware
Voltage and current sensing
Temperature sensors
Connectors
Insulation
Switching and protection components
Studies of electric-aircraft battery integration have shown that packaging, thermal management, and supporting hardware can create a substantial difference between cell-level and pack-level specific energy. (U.S. Department of Energy OSTI: Electric Aircraft Battery Integration)
For this reason, we recommend that an OEM provide two different figures when discussing a lightweight battery:
Cell specific energy
and
Maximum complete operational battery weight.
The second figure is usually more important to the aircraft designer.
A requirement such as "the battery must stay below a certain mass" should specify whether that number includes the BMS, enclosure, cables, and connectors.
Peak Power and Climb Power Are Not the Same Requirement
An electric paramotor does not draw constant power throughout the flight.
Takeoff can create a high propulsion load. Climb may require substantial power for a longer period. Once the aircraft is established in flight, required power may fall.
Battery specifications should reflect those different conditions.
Instead of writing:
Peak power: 20 kW
a more useful engineering specification would be:
Peak power: 20 kW for a defined duration, at a defined SOC and temperature.
The same applies to continuous current.
A battery that can supply a current for several seconds is not automatically able to sustain the same current for several minutes without unacceptable voltage sag or temperature rise.
When we evaluate propulsion batteries, we therefore want to know:
Takeoff
What is the maximum electrical power, and how long can the takeoff phase last?
Climb
What power needs to be maintained after takeoff, and for how many minutes?
Cruise
What is the typical steady-state power once altitude and flight speed stabilize?
Low-SOC Operation
How much power must still be available when the battery is no longer near full charge?
This last point is particularly important. A battery can look strong during a full-charge bench test and behave differently later in the flight as cell voltage falls and internal losses become more visible.
How System Voltage Changes Battery Current
Voltage architecture strongly affects the current required from the battery.
A useful first approximation is:
Current ≈ Power / Voltage
For an illustrative 15 kW electrical load:
| Battery Voltage | Approximate Current |
|---|---|
| 50V | 300A |
| 75V | 200A |
| 100V | 150A |
These values ignore conversion losses, but the relationship is useful during early system design.
Higher voltage reduces current for the same electrical power.
That can matter because conductor losses follow approximately:
Power Loss = I²R
Reducing current can therefore reduce resistive loss in cables, busbars, connectors, and other conductive paths.
Research into aircraft electrical systems also treats voltage architecture and changing flight-phase power demand as important system-design variables rather than isolated component choices. (German Aerospace Center: Aircraft Power Requirements Across Flight Phases)
Higher voltage is not automatically better.
The following systems must all support the selected voltage:
Motor controller
BMS
Connectors
Cables
Insulation
Charger
Service procedures
Electrical protection
At Grepow, we prefer the battery voltage to be selected together with the motor and controller rather than after the propulsion architecture has already been finalized.
Lightweight, High-Power, or Long-Endurance?
When developing an electric paramotor battery, it helps to identify the primary design priority early.
Lightweight Configuration
The priority is reducing complete battery mass.
Capacity is selected around the required mission rather than maximum possible endurance.
High-Power Configuration
The challenge is maintaining loaded voltage during takeoff or climb.
Cell resistance, discharge capability, thermal behavior, conductors, and connections become particularly important.
Long-Endurance Configuration
The goal is carrying more usable energy without allowing the battery to dominate aircraft mass.
High specific energy and efficient pack integration become more important.
Balanced Configuration
Most propulsion batteries require some combination of all three.
Research into aviation battery development similarly emphasizes trade-offs among specific energy, power, safety, temperature behavior, and system integration instead of maximizing one battery metric in isolation. (Applied Energy: Battery Technology for Sustainable Aviation)
For us, that is the most useful way to think about paramotor battery design:
not the highest kWh, highest C-rate, or highest Wh/kg - but the battery that best fits the aircraft mission.
What Should You Send a Battery Manufacturer?
A clear aircraft requirement can shorten the battery-development process considerably.
When discussing an electric paramotor or motorized paraglider project with Grepow, these specifications give us a useful starting point:
Target flight time or mission profile.
Estimated battery energy requirement.
Maximum complete battery weight.
Nominal and maximum system voltage.
Peak motor power and required duration.
Sustained climb power and duration.
Typical cruise or average power.
Maximum battery dimensions.
Motor and controller specifications.
Required BMS communication, such as CAN.
Operating-temperature range.
Charging requirements.
Prototype quantity and expected production volume.
Mechanical drawings are also useful when installation space is limited.
The earlier battery design is considered together with the motor, controller, frame, mounting system, and aircraft weight budget, the easier it is to avoid late-stage compromises.
Conclusion
Sizing an electric paramotor battery is not primarily a question of choosing a kWh number.
The battery has to store enough energy for the intended flight while staying within a practical mass budget. It must deliver takeoff and climb power, operate within the selected voltage architecture, and leave enough weight and space for the BMS, enclosure, conductors, connectors, and protection structure.
The engineering principles are not completely new.
Grepow already works with many of the same energy, power, weight, thermal, and integration challenges in professional UAV and electric aviation battery systems. Those lessons provide a strong starting point for motorized paraglider projects.
The application still has to be designed and validated on its own terms.
For that reason, we size an electric paramotor battery around the complete aircraft mission:
mission energy + complete pack weight + peak power + sustained power + system voltage + installation constraints.
That gives both the aircraft developer and the battery manufacturer a more useful engineering target than choosing a pack by Ah or kWh alone.
FAQ
I'm building my first electric paramotor. How many kWh of battery should I use?
There is no fixed capacity for every electric paramotor. Start with flight time, propulsion power, aircraft weight, and maximum battery mass, then calculate the energy required for the complete mission rather than choosing the largest battery that fits.
Will a larger battery always give my paramotor more flight time?
A larger battery stores more energy but also adds weight. The useful comparison is how much additional flight time the extra energy provides after the added battery mass and its effect on the aircraft are considered.
We're designing a high-power electric paramotor. What should we specify besides peak motor power?
Provide peak-power duration, sustained climb power, cruise power, system voltage, operating SOC range, temperature conditions, battery dimensions, and complete pack-weight limit. Power without a required duration is not enough to select the correct battery.
Should an OEM compare batteries using cell Wh/kg or complete pack Wh/kg?
Both are useful, but aircraft sizing should focus on the complete operational pack. BMS hardware, enclosure, conductors, connectors, sensing, insulation, and structural components all add weight beyond the cells.
Can UAV battery experience be directly transferred to an electric paramotor?
Many engineering principles transfer, including energy-density optimization, high-power discharge, thermal monitoring, BMS communication, and pack integration. A pilot-carrying aircraft still requires application-specific mechanical, electrical, safety, and propulsion-system validation.
