UAV Battery Procurement and Selection Guide

1 UAV battery procurement process

A UAV battery purchase concerns an electrical system that must perform a defined mission repeatedly. Capacity, energy density, rate and price are starting points. The decision must establish whether the system can supply the required power, fit the aircraft, support the schedule and remain consistent in repeat orders under the intended payload, weather and reserve policy.

This guide is for UAV manufacturers, system integrators and professional operators. Eliminate configurations that fail mission, voltage or mass limits, then compare cell energy, output, installation and turnaround. Use the result to prepare a sample plan and a purchasing specification. Chapter 6 is an illustrative screening case; its aircraft, mission, mass limit, cost and derating inputs are assumptions.

Keep three decisions separate: reject because a hard constraint fails; hold because evidence is missing; or shortlist for sample validation. Missing evidence is not a pass. Strong price or density scores cannot compensate for incompatible voltage, discharge duty or installation.

2 Technology routes and product forms

Separate three dimensions when reading high-energy, semi-solid, anode-free and pouch claims. Form describes packaging; electrode architecture describes energy storage; electrolyte and separator design describe ion transport and separation. A single label does not establish all three, or prove endurance, power, life or safety.

QuantumScape describes an anode formed during initial charging, with a solid separator and organic liquid catholyte. This clarifies terminology, not Golden Feather construction. Molicel’s cylindrical P45B specifies 45 A continuous discharge with an 80°C cutoff, disproving the assumption that cylindrical means low power. That cutoff is not a recommended UAV operating temperature. [R1][R2]

Choose between energy, output and turnaround

Endurance emphasizes usable energy and aircraft mass. Heavy climbing, repeated take-off and aggressive manoeuvring emphasize loaded voltage, sustained current and heat. High utilization also depends on charging, cooling and spare packs. Optimize operating results after meeting the mission, rather than maximizing one number.

Research, engineering, customer-validation and production samples support different evidence. Ask about supply maturity, sample-to-production differences, expected changes and available records. A technical development does not automatically qualify a battery for an aircraft.

3 Reading battery specifications

Capacity, energy and power answer different questions

Ah expresses charge capacity, Wh energy and W instantaneous power. Nominal voltage times rated Ah gives nominal Wh. Usable energy comes from discharge data under defined cutoffs, temperature, current and ageing. Comparing Ah across voltages is misleading. A typical capacity must not replace a rated or minimum contractual value.

Use the datasheet capacity basis for C-rate conversion. For 20 Ah, 3C is 60 A. This does not establish duration, temperature, cutoff or the pack limit. Pulses need duration, interval and thermal state. A two-minute take-off cannot use a ten-second peak rating.

Separate cell density from pack metrics

Cell density is a legitimate priority. Cell-specific energy uses cell-level Wh and kg; volumetric density uses cell-level Wh and litres, with capacity, voltage, mass, volume and state defined. Leads, connectors, wrap, supports and protection affect pack mass and envelope. Pack appearance cannot establish or discredit original cell density.

Keep the supplier’s cell specific-energy declaration, comparisons calculated from the same cell specification, and pack installation data in separate fields. If only a series range is supplied, request the proposed model and revision with its measurement conditions. Use the matching test report or approved specification to agree the supplied rating. Pack mass and installation dimensions serve aircraft integration and do not replace cell ratings.

4 Application requirements

Application names identify questions, not compatibility. Spraying reduces payload; logistics outbound and return loads differ. Obtain phased logs covering the heaviest payload, adverse return and temperature boundaries. State whether sampling can capture peaks.

Without flight data, aircraft-side motor, propeller, controller and payload estimates can support screening. Replace them with measurements during sampling. Label estimates so an endurance target does not become a verified supplier promise.

Long-endurance inspection and mapping

Inspection buyers often trade a longer route against sensor payload. Fix the payload and take-off mass limit before comparing usable Wh and voltage late in the return leg. Higher cell specific energy can free a mass budget for energy or payload, while take-off, headwind return and late-mission loads must still be supported. Do not add these benefits together without aircraft validation.

AEP49Ah and ECP39Ah are two directions to discuss. AEP49Ah offers an energy/mass comparison but its 1C maximum discharge and 0.2C charge limit load and turnaround. ECP39Ah uses a 4.20 V charging platform and a 5C maximum discharge rating for a different screening path. Calculate current, total mass and full-charge voltage for the proposed S/P configuration before sampling. Change the configuration if a two-minute demand exceeds its allowed current or return-leg voltage is insufficient.

Agricultural spraying and repeated sorties

Agricultural purchasing should focus on completed daily work. Check current and sag at fully loaded take-off, then use phase-specific power records as spraying reduces mass. Cooling, charging and swapping determine the next departure. FAP22Ah and FAP30Ah are candidates for a charging/output discussion and both use a 4.35 V charge ceiling. Greater capacity changes mass and installation space, so choosing the larger Ah figure alone is insufficient.

First exclude an incompatible charging platform, a thermal condition that prevents the required charge rate, or inadequate site power. Then compare spare-pack and charging-channel combinations. The 5C maximum charge rating is not an instruction for every temperature or a promise of a 12-minute full charge. Chapter 9 separates inventory from throughput; the actual SOC window and shared charger power will change the result.

Heavy-lift logistics and VTOL fixed-wing aircraft

Heavy-lift logistics combines an extended high-power stage with a battery mass limit. VTOL fixed-wing aircraft combine cruise energy demand with take-off, transition and go-around output. List current, duration and repetition for each phase, especially a go-around at low SOC. A low cruise average must not hide a take-off or landing constraint.

ECP39Ah, FAP models and PCP45Ah can enter discussions under different voltage, capacity and charging requirements, each with a defined configuration. A 10- or 60-second pulse cannot cover a longer hover. Twelve PCP45Ah cells alone weigh about 9.168 kg; a project with a 7 kg pack budget should reject that 12S1P configuration at the RFQ stage. Application labels guide evaluation; the shortlist must meet the aircraft’s mass, voltage, thermal and mission-load limits.

5 Cell comparison

These six models span energy-oriented, fast-charge/output and alternative-capacity platforms. Values are cell declarations from cited revisions, not pack or aircraft qualifications. The table does not rank prices.

Apply temperature conditions. AEP49Ah permits maximum 1C discharge at 0–45°C and no more than 0.3C at −20 to 0°C. FAP30Ah’s −10°C charging test uses 1C, not its maximum 5C. PCP20Ah and 45Ah specify 0.1C charging at −15°C. [S1][S3][S5][S6]

Align life-test conditions

ECP39Ah lists 300 cycles at 1C charge/3C discharge and 600 at 0.5C/0.5C, both to at least 80% capacity. FAP30Ah’s 1,000 cycles use 5C/10C at 25±3°C with defined cutoffs and rests; PCP20Ah uses 1C/1C. Counts alone cannot rank these or establish equal flight sorties. [S3][S4][S5]

Resolve version conflicts. EBP110105230-50Ah A3 specifies a 4.20 V charging cutoff while a differently dated catalogue gives 4.25 V. Do not select the higher value or borrow from a similar model. Confirm delivery revision, charger settings and corrected documentation in the order. [S7]

Read energy, mass and mission limits together

The table uses rated Ah times nominal voltage for nominal Wh and the mass from the same cell specification. The next table gives a cell-level specific-energy comparison to support cell mass budgeting. This differs from measured Wh/kg obtained by integrating a defined discharge curve.

Comparing cell specific energy

The comparisons use nominal cell masses, each with a ±5 g tolerance. They include no external wiring, pack packaging or pack dimensions and are not supplier-guaranteed minimum specific-energy ratings. Use them for screening, not to predict usable energy at high current, low temperature or end of life. Agree the cell revision, energy-test current and temperature, voltage limits, cell mass and acceptance method for a purchased specific-energy guarantee. Confirm Wh/L separately using cell body volume in an agreed state.

The catalogue dated 25 September 2025 separately describes the Wuji series as 450–550 Wh/kg, the agricultural series as approximately 210 Wh/kg, and ECP models under the “340 series.” These remain supplier series descriptions. Model-specific purchasing uses the matching approved specification; series descriptions and the nominal calculations above serve different purposes. [S9]

Screen current ratings with their temperature conditions

“Maximum discharge” follows the specification wording. It does not establish unrestricted pack operation at every SOC, temperature or cooling condition. Obtain discharge curves and thermal conditions for a two-minute climb or repeated pulses, then validate the pack. The AEP49Ah discharge-performance clause specifies more than 80% capacity retention after 20 cycles at 0.3C, 25±3°C and 0 MPa. Agree service-life requirements against the actual mission duty. [S1–S6]

Turn a cell shortlist into a custom RFQ

These are custom-evaluation paths, not automatic substitutions for catalogue packs. Send New Journey the full cell model, specification revision and mission brief to confirm availability, proposed S/P configuration and sample scope. Add a finished-pack model and its relevant documents to the quotation once the configuration mapping is established.

6 Screening case From electrical limits to mass and validation

This hypothetical 34-minute inspection mission demonstrates the method, not a delivered aircraft. Assume a 36–52 V electrical window. Power is measured at the battery output, so motor/controller efficiency must not be deducted again. Payload and flight method are fixed for this budget.

Step 1 Calculate required nominal energy

Phase energy equals power × minutes ÷ 60. Assume 15% is withheld from normal mission use, an ageing capacity factor of 0.90 and a combined temperature/rate factor of 0.95. Required nominal energy is 580 ÷ (0.85 × 0.90 × 0.95) = 798.1 Wh. Replace these assumptions with operational rules and measurements. Do not deduct losses already included in measured energy.

For an abstract comparison, 12S at 3.6 V nominal per cell and 20 Ah gives 864 Wh; 16 Ah gives 691.2 Wh. The latter fails; the former passes only the energy screen. Added capacity may increase aircraft mass and power, so added Wh do not necessarily produce proportional endurance.

Step 2 Check voltage and sustained current

At 12S, 4.20 V per cell gives 50.4 V full charge, within the assumed ceiling. At 4.35 V, 52.2 V exceeds it. A revised charging limit needs manufacturer-supported capacity, balancing and charging validation; original full-charge energy cannot simply be retained.

At 36 V, take-off requires 2200 W ÷ 36 V = 61.1 A. For 20 Ah, 1P, this is about 3.06C for two minutes. A candidate with a 3C/60 A maximum discharge rating does not pass because the values are close. A ten-second peak cannot cover two minutes. Revise the candidate, configuration or mission, then verify sag and heating.

Step 3 Retain configurations for mass and installation review

The 16Ah energy example and the 52.2 V configuration without a system redesign are excluded first. Remaining options must satisfy the two-minute 61.1 A demand, return-leg voltage, mass, fit and thermal limits. Check both remaining energy and loaded voltage: unused Ah will not prevent an interruption if voltage sag triggers protection.

Retain assumptions, calculations, rejection reasons, open tests and data owners. Revisit the power budget when payload, propeller, flight method or battery mass changes rather than editing only the capacity entry.

Apply the example constraints to actual candidates

These are the stated voltage/current screens under an assumed room-temperature condition, not aircraft qualification. The two retained models differ in capacity, mass and operating window. Feed actual pack mass back into the mission model and check loaded voltage, heat and charging. Other capacities or configurations may also merit investigation.

Step 4 Eliminate configurations above the pack mass limit

Add an explicit assumption: the aircraft allows a complete installed pack mass of 7.00 kg, including cells, interconnects, insulation, harness, protection and restraints. Twelve ECP39Ah cells have a nominal combined mass of 12 × 0.430 = 5.160 kg; twelve PCP45Ah cells total 12 × 0.764 = 9.168 kg. These are cell-mass sums, not measured pack masses or a conversion of cell density.

The ECP option’s 1.780 kg allowance is a budget, not proof that the remaining components fit it. List structural, connection and electronic masses, then weigh the assembled sample. Recalculate after changes to parallel count, enclosure or protection. PCP45Ah is rejected for this example’s 7 kg limit, not for aircraft with a larger mass allowance.

Step 5 Complete drawing and late-mission load checks

Start installation review with the customer’s bay drawing, rather than multiplying cell dimensions alone. ECP39Ah specifies an initial thickness limit of 11 mm measured with a 2000 gf PPG, and a 13.2 mm limit after the cycles in specification section 6.1.2, a width limit of 88 mm and a length limit of 189 mm. Use the relevant state in the pack drawing and add insulation, connections, structure, lead exits and connector service space. [S4] No bay geometry is assumed in this example, so fit remains a drawing-review requirement.

A 12S1P ECP39Ah configuration has 12 × 3.6 × 39 = 1684.8 Wh nominal energy. Applying the illustrative factors gives a 1224.4 Wh budgeted usable value, above the 580 Wh mission estimate. This only means energy is not the first exclusion under those assumptions; it is not a 34-minute flight guarantee. The power profile must match actual payload and pack mass. After weighing the sample, obtain phase power for that aircraft, payload and mission, then recalculate energy and reserve.

This example retains ECP39Ah 12S1P for engineering-sample evaluation, excludes PCP45Ah 12S1P on mass and excludes the other candidates on the stated electrical constraints. The next purchasing step is to agree the pack drawing, component mass budget and mission test plan before a production order.

7 Battery pack customization

Cell current capability is not pack capability. Interconnects, welds, protection, fuses, connectors, cables and cooling constrain output. Parallel arrangements require current-sharing, symmetry and consistency checks. A cell C-rate calculation alone is not a pack guarantee.

The 86.4 V, 39 Ah, 24S1P pack specification lists 117 A continuous, 195 A for three minutes and a 100.8 V charge cutoff. [S8] Use those pack limits. A separate 39 Ah cell’s 5C entry cannot rewrite this pack’s continuous limit without verified cell/configuration mapping.

Monitoring, protection and balancing are separate functions. TI’s reference design implements sensing, protection switching and balancing distinctly, showing why “with BMS” is insufficient. [R3] Aircraft engineering must coordinate alarms, power limits, return decisions and protection. Necessary protection should not be disabled to avoid interruption.

Finish customization with an agreed configuration list: cell revision, operating window, interfaces/firmware, components requiring substitution approval and the associated test plan. This is the basis for production consistency and anomaly tracing.

8 Battery bay, swelling and temperature

A bay must accommodate the specified operating envelope, not just a new uncharged cell. AEP49Ah lists 8.3 mm at 0% SOC, 11.6±0.5 mm at 100% SOC, and 14±0.5 mm at 100% SOC after 20 cycles without pressure. [S1] These are different states, not measurement error.

Request state-defined drawings and check permitted restraint, mounting, connector access, lead bends and insulation. Do not invent clamping force or support mass by wires. Translate cell parameters into pack installation requirements, then validate vibration, temperature changes and repeated removal.

Treat charging, discharging and storage temperatures separately. Minimum discharge temperature does not authorize charging there; maximum rate is not an all-temperature rating. Identify ambient, surface, internal and connection measurement points, including post-operation temperature rise. Immediate fast charging after landing needs real-condition validation.

Write water, dust, cold and vibration requirements as conditions and test methods. Apply a rating only to matching model, sealing, construction and scope. A cell test or different enclosure rating does not qualify the current pack.

9 Charging schedule and spare batteries

“5C means a full charge in twelve minutes” ignores the process. Charging commonly includes constant-current and constant-voltage phases with tapering current. [R4] Turnaround also includes inspection, cooling, connection, balancing and queues. Compare matching SOC windows, temperatures, termination and pack configurations.

A scheduling example for one aircraft

Assume a departure every ten minutes: eight flying, two swapping. A pack needs 38 minutes after landing to become ready, including 30 minutes occupying a charger channel. Pack one lands at minute 8 and is ready at 46. Departures at 0, 10, 20, 30 and 40 therefore need five packs. Four creates a wait at minute 40.

Two channels finish at most two packs per 30 minutes while demand is one per ten minutes. At least three simultaneous channels match the ideal average rate, with additional allowance for delays and shared power. More inventory postpones but cannot eliminate a persistent throughput deficit.

Combine schedules and power budgets for multiple aircraft. Multi-port chargers may share total power; include losses and other site loads. An RFQ should state SOC window, sorties, available power, acceptable waiting and spare-pack budget to compare complete operating costs.

10 Sample testing and acceptance

Freeze configuration and method before testing: inputs, instruments, temperature, SOC, load, logging rate, criteria and owner. Link results to sample serials, cell lots, structure and firmware. A “passed” screenshot does not support repeat procurement.

Replay normal and agreed adverse cases, including a late-mission climb or cold return, rather than only brief full-charge room-temperature discharge. Set sample count by risk, variation and purpose. A few successful samples do not establish zero production defects.

Progress through bench, integration, controlled flight and pilot use. Preserve logs and sample state after anomalies, determine cause and changes, then repeat affected tests. Destructive overcharge, crush or penetration tests require capable facilities and are not introductory customer procedures.

Agree project acceptance values such as late-mission minimum voltage, temperature limits at defined points, charge termination, envelope and permissible variation. Datasheet extremes should not automatically become normal-operation targets. Engineering defines operating limits and margins, then confirms them by testing.

11 Cost per completed mission

Low price need not mean low total cost; high cycle count need not mean low operating cost. Qualify the mission first, then compare battery allocation, charging equipment, inventory, maintenance and downtime per useful mission. A useful mission meets payload, duration and return requirements; laboratory cycles are not a substitute.

Illustratively, A costs USD 420 and completes 240 useful missions: USD 1.75 each for battery purchase alone. B costs USD 600 and completes 500: USD 1.20. If B achieves 300, it becomes USD 2.00 and the ranking reverses. These hypothetical prices and counts illustrate sensitivity, not supplier quotations.

Compare conservative, baseline and favourable outcomes, including extra chargers, power and spares. Retirement must reflect mission performance: capacity alone does not override excessive sag, heat, physical deterioration or connection problems. Agree service scope, exclusions, records, isolation and remedy procedures. Warranty, response times and compensation belong in the contract.

12 Delivery documents and revision control

Separate selection documents, sample/lot validation records and transport/compliance evidence. Similar titles do not establish equal scope. Check model, manufacturer, report number, revision and tested object.

IATA distinguishes lithium-ion/lithium-metal and standalone, packed-with-equipment or contained-in-equipment arrangements. A UN 38.3 summary identifies model, manufacturer, laboratory, report and tests; an SDS is not that summary. An anode-free lithium-metal product is not automatically ordinary lithium-ion because it is rechargeable. Use matching product records and carrier requirements. [R5]

Critical changes include cells/revisions, protection, harness/connectors, structure, charging and firmware. Agree notice, approval and revalidation requirements. Matching photographs do not prove an unchanged version; an existing report does not cover every specification or use.

13 New Journey customization support

Xiamen New Journey Technology Co., Ltd. supports UAV battery customization through technical work on high-energy-cell applications, pack configurations and aircraft interfaces. The useful outcome is a comparable, verifiable, deliverable configuration rather than a capacity recommendation alone.

Start with cell screening, configuration, voltage, output and charging, then define samples around the bay, harness, connectors and communication. Obtain missing aircraft load inputs instead of treating battery specifications as aircraft validation.

This is a scope to agree per project, not an automatic contract. Confirm model availability, schedule, validation, costs and service after assessment. The battery party owns agreed configuration and records; aircraft engineering owns integration, flight-control strategy and operation. Both agree interface and validation boundaries.

Technical credibility rests on delivery evidence the customer can review: matching specifications, sample records, lot traceability, change control and anomaly handling. Agree which documents each stage requires, who provides them and how they are accepted so selection decisions carry through into supply.

Example project configuration and test records

Use the blank template below to agree the scope of work. It shows a proposed document structure, not a completed customer project or test report. Add the responsible people, revisions and acceptance values for the actual project.

Prepare the Chapter 14 mission brief to discuss candidate cells, pack configuration and a sample plan with New Journey. The catalogue shows the existing range; custom projects are assessed against the actual mission.

View the UAV battery catalogue

Contact New Journey about a project

14 RFQ inputs and purchasing checklist

Use the companion customer project brief for an RFQ and attach bay drawings and available load logs. If the model is undecided, start with the mission and hard limits. Assign owners and dates to missing inputs. The blank configuration and test record template below connects the initial discussion to sample approval and reorders.

Decide each item before sample approval and ordering

First check full voltage, late-mission voltage/energy, current and peak duration, temperature, charged/aged dimensions, interfaces and protection. A hard failure requires rejection or redesign. Then check sample revision, charging throughput, pilot variation, matching documents, acceptance, changes and service. Keep evidence gaps open rather than averaging them away.

Finish with a one-page decision: candidate/revision, reasons it suits the task, rejected alternatives, outstanding tests, sample plan and purchase conditions. Compare endurance, efficiency, total cost and delivery risk only after hard constraints pass.

Download the customer project brief XLSX

Download the blank configuration and test record CSV

Appendix Terms and references

References checked to 25 October 2026. S references are supplied model documents; R references are public primary sources. They support definitions, parameters and methods, not third-party validation of the example aircraft or all New Journey products.

[S1] AEP8390192-49Ah, GF-PS-24032 A2, 2024-11-19, pp. 5–7

[S2] FAP10790192-22Ah, GF-PS-25008 A0, 2025-02-21, pp. 5–6

[S3] FAP105105230-30Ah, GF-PS-24026 A1, 2024-11-11, pp. 5–7

[S4] ECP11087188-39Ah, GF-PS-23016 A2, 2024-11-11, pp. 4–7

[S5] PCP10090192-20Ah, GF-PS-25069 A0, 2025-06-04, pp. 4–7

[S6] PCP104136260-45Ah, GF-PS-25038 A1, 2025-06-03, pp. 4–7

[S7] EBP110105230-50Ah, GF-PS-24071 A3, 2025-08-18; catalogue 2025-09-25

[S8] 86.4V39Ah PACK A0; revision record 2024-09-27, cover 2025-08-25

[S9] Golden Feather product catalogue, 2025-09-25, pp. 1–2; series descriptions

[R1] QuantumScape Battery Technology

[R2] Molicel INR-21700-P45B datasheet, version 1.4

[R3] Texas Instruments TIDA-00449 reference design

[R4] Texas Instruments SNVA557 charging discussion

[R5] IATA Battery Guidance Document, revised 2026