Matti Blume · CC BY-SA 4.0 · Falcon 8X in flight (Paris Air Show 2019)The Falcon 8X extends the 7X lineage through aerodynamic changes, engine optimization and additional fuel capacity. First deliveries took place in October 2016. The selected background reference covers the 7X and 8X, with figures labelled by model. The simulator listing records its product's development status.
Falcon 8X: manufacturer specifications
Dassault’s announcement dates the first flight to 6 February 2015 at Bordeaux-Mérignac. Eric Gérard and Hervé Laverne flew the first prototype, beginning the airborne phase of a programme whose remaining test and certification work lay ahead.
First flight: 7X: 5 May 2005 8X: 6 February 2015
Developed from: Dassault Falcon 900
Dassault quotes a 107 KIAS reference approach speed at typical landing weight. That condition belongs with the number: it is not a single approach speed for every weight and configuration. The 8X uses digital flight controls and three PW307D engines.
George encountered the 8X as a working test aircraft, with ballast tanks and instrumentation taking the place of a finished passenger cabin. Gérard occupied the right seat and Lascourrèges the jumpseat. He assessed handling during development in a test aircraft.
The first moments of taxiing required adjustment to the steering and brakes, which initially felt sensitive. Once flying, George appreciated the sidestick’s balance of pitch and roll forces and the feedback through his hand. His account follows the process of becoming comfortable with unfamiliar controls, keeping those personal impressions separate from the performance work still belonging to the wider test programme.
Gérard and Laverne took the first Falcon 8X prototype into the air from Bordeaux-Mérignac for a flight lasting one hour and forty-five minutes. The programme included handling checks, system tests and a climb to high altitude before the crew returned to the departure airport. It was the beginning of the aircraft’s flying test campaign.
Gérard described the experience with pride, saying the flight had met its objectives and exceeded some of them. He felt honoured to participate and expressed confidence about the work ahead. Those remarks record the pilot’s reaction to a successful first outing; his optimism concerned a programme still to be completed, rather than an announcement that development or certification had already finished.
A simulator session gave Thurber time to explore the 8X’s controls before flying the aircraft at Istres the next day. In the air, small sidestick movements soon felt comfortable, although steep turns were less tidy when he worked against the stick’s resistance. He became more familiar with the aircraft through the manoeuvres.
The return included his first actual traffic-collision avoidance resolution advisory, followed by a landing that needed correction after he began the flare too high. A little additional power helped produce a smooth arrival.
The Falcon 8X extends the 7X lineage through aerodynamic changes, engine optimization and additional fuel capacity. First deliveries took place in October 2016. The selected background reference covers the 7X and 8X, with figures labelled by model. The simulator listing records its product's development status.
This starting point selects Dassault Falcon 8X. Its aircraft-level settings do not select a particular developer’s custom systems.
The fixed-centre choice represents an electronic-control inceptor. The spring stays independent of airspeed. Directed aerodynamic loading is omitted. Enabled travel curves shape pitch and roll resistance separately.
Aircraft trim is separate from the configured hardware centre. Aircraft trim retains the fixed hardware centre. Autopilot following is off.
The Falcon 8X extends the 7X through aerodynamic changes, optimized engines and additional fuel capacity. Deliveries began in October 2016. Its electronic flight-control background belongs to this later aircraft, while the simulator’s development status is a separate product fact.
The gains are normalized profile settings. They describe the chosen effect balance; hand force depends on the device and its output limits. IAS references are tuning values rather than operating limits. Physical acceptance of this revision remains pending.
施加于模型产出的一切、在设备上限之前的最终整体输出缩放。
调高: 一切(弹簧、载荷、效果)一同增强。
调低: 一切一同变柔。
设定理由: Scales overall profile strength while preserving effect balance, subject to device and output limits.
把摇杆拉回中央的基础回中力。其他所有力都叠加在它之上。太低,正常飞行中摇杆会发软;太高,它会与你的手较劲,并掩盖叠加其上的细微提示。
调高: 更硬的回中,更抗手。
调低: 更软的杆,只靠气动载荷。
设定理由: The fixed-centre choice represents an electronic-control inceptor. The baseline spring is 0.55. The electronic-control law keeps centering independent of airspeed.
Dassault DFCS backgrounder中央附近弹簧保持安静的小中立区,让静止时的微小移动不会咔嗒作响。更宽更安稳但更松,更窄更精确但可能在中央附近抖动。
调高: 更安静但更松的中央,旷量更大。
调低: 更紧的中央,静止时可能抖动。
设定理由: Sets travel around the centre before the baseline spring resists. Smaller values engage it sooner.
设定理由: The centre preload is 0.03. It ramps outside the 0.01 deadband across 0.05 travel, shaping the passive centre independently of aircraft autotrim.
设定理由: Sets the travel used to ramp in centre preload. Wider intervals make its onset more gradual.
作用于两条持续轴载荷的主缩放,在它们各自的独立平衡之前施加。配置文件通常不动它,而是调校两条轴载荷。
调高: 两轴载荷一同加重。
调低: 两轴一同减轻。
设定理由: The stored 0.04 aerodynamic-load gain is inactive under the fixed-centre control law.
启用低速弹簧介入窗口(上面的起始/全强度节数)。关闭时弹簧在所有速度下恒定。
设定理由: Allows baseline spring strength to rise with indicated airspeed where the control law permits it.
在静止、空速尚未产生气动力之前,弹簧还剩多少。下限高,停机时摇杆结实;下限低,则是停放轻型飞机那种钢索松弛的感觉。
调高: 停机和滑行时杆更结实。
调低: 停机时杆发软,只随速度苏醒。
设定理由: Sets low-speed spring strength as a fraction of baseline when blending is enabled. One keeps full strength.
弹簧从低速下限开始向全强度攀升的空速:起飞滑跑中操纵面"苏醒"的那一刻。
设定理由: Sets the IAS where the low-speed spring blend starts rising. This is a feel threshold, not a flight limit.
弹簧达到全强度的空速。从起点到这里,随着气流在操纵面上增强,回中逐渐变硬。
设定理由: Sets the IAS where the low-speed blend reaches baseline strength; high-speed stiffening also uses it.
气动载荷达到设计满值的指示空速。它把整条载荷曲线锚定在飞机真实的速度范围:172在110节就载满,喷气机要晚得多。
调高: 载荷来得更晚;杆轻到更高速度。
调低: 载荷来得更早,巡航更沉。
设定理由: Sets the IAS reference for aerodynamic loading. It is an estimate, not published cruise TAS or a flight limit.
在偏转载荷之外,回中本身随速度变硬的程度。零则中央手感恒定;越大,巡航时回中越硬,起落航线上越松。
调高: 中央随速度明显变硬。
调低: 任何速度下中央手感恒定。
设定理由: Adds permitted spring resistance above the full-blend speed. Zero removes this high-speed increase.
速度驱动的中央变硬上限,防止高速飞行把弹簧无限上紧。
调高: 高速允许更多总硬化。
调低: 硬化更早封顶。
设定理由: Limits the squared airspeed ratio used for high-speed spring stiffening; it is not a device-force cap.
由副翼偏转和空速产生的持续横滚载荷,独立于俯仰调校。与升降舵载荷一起,决定评测中常说的操纵协调比。
调高: 横滚力更重。
调低: 副翼更轻更灵。
设定理由: Roll and pitch aerodynamic scales are 1 and 1, respectively. These stored weights do not create directed aerodynamic loading while that term is inactive. The pitch spring-travel curve reaches output 1 at input 1. The roll spring-travel curve reaches output 0.3 at input 1. Spring-travel response contributes separately to axis balance.
由升降舵偏转和空速产生的持续俯仰载荷,独立于横滚调校。这是决定机型俯仰重量的主杠杆。它不影响副翼、弹簧、配平或抖振力。
调高: 速度下持续俯仰力更重。
调低: 升降舵更轻,握持更省力。
设定理由: Scales pitch aerodynamic loading; pitch spring travel and trim responses are separate settings.
每个稳态俯仰或横滚力到达设备前的上限,防止猛烈机动中砸击或饱和硬件。
调高: 削波前更高的稳态力峰值。
调低: 更柔的上限;猛烈机动更早被抹平。
设定理由: Caps directed-force output. Native spring effects and device limits remain separate.
升降舵配平缓解持续俯仰力、移动杆的安定位置的强度。在100 %时,配平得当的飞机不需要保持压力——正是真实飞行中"用配平消掉载荷"的流程。
调高: 配平消掉更多持续力;100 %时满配平可完全抵消。
调低: 即使配平也仍要持续用力。
设定理由: Aircraft trim is separate from the configured hardware centre. Pitch relief is off, with stored authority 0; roll authority is 0.
Dassault DFCS backgrounder横滚配平的同类缓解。多数通航机型没有真正的副翼配平,所以保持为零;有横滚配平的机型获得相应的值。
调高: 横滚配平消掉更多持续力。
调低: 横滚配平作用更小。
设定理由: Scales supported roll-trim relief and permitted centre movement. Zero removes roll response.
由轮速和地面类型(铺装、草地、砾石)产生的滚动振动。
调高: 杆上更强的地面质感。
调低: 更平滑的滑行。
设定理由: Sets rolling texture strength, modified by speed, surface and undercarriage configuration.
来自伸缩缝、车辙和粗糙地面的短促离散颠簸,为持续隆隆声打上标点。
调高: 接缝与车辙的冲击更清晰。
调低: 更柔的地面细节。
设定理由: Sets gear-bump texture during ground motion, separate from touchdown impact.
接近失速及失速警告响起时的机体抖动:这副机翼宣告不满的音量。断失干脆的机型抖振收敛,让喇叭承担警告。
调高: 更强的失速前颤抖。
调低: 更含蓄的机翼;警告交给喇叭。
设定理由: Sets stall-buffet strength. Zero removes the cue without changing simulator stalls or warnings.
接近马赫极限的跨音速抖振。对接近MMO的喷气机有意义,对到不了那里的活塞机和涡桨机为零。
调高: 接近马赫极限时更强的跨音速抖振。
调低: 高马赫下更平滑的飞行。
设定理由: Sets high-Mach buffet strength; onset and full-strength thresholds are separate.
襟翼伸入气流后机体的低频振动,发生在它们真正做功的速度窗口内。
调高: 襟翼做功时更粗糙的飞行。
调低: 更柔的进近襟翼。
设定理由: Sets flap buffet at the configured position and speed gates. Flap movement texture is separate.
可收放起落架悬在气流中引起的机体鼓振。固定起落架机型为零,它们的机体外形从不改变。
调高: 放起落架时更多鼓振。
调低: 放起落架飞行更干净。
设定理由: Sets gear aerodynamic buffet; movement and ground-contact cues are separate.
由飞机自身失速警告系统触发的专用抖杆器振动。只有真有抖杆器的机型才有值;其余全靠气动抖振和喇叭。
调高: 更硬的抖杆器。
调低: 更含蓄的抖杆器。
设定理由: Sets triggered shaker strength; inactive while the shaker feature is disabled.
机轮触及跑道那一下的单次冲击,按下沉率缩放:轻柔着陆是耳语,结实到达是一记闷响。
调高: 触地时更硬的一击。
调低: 更柔的到达。
设定理由: Sets landing-impact strength; landing telemetry and response shape determine the pulse.
反推或桨叶beta区工作时的滑跑振动。无反推机型为零。
调高: 反推下更粗糙的滑跑。
调低: 更含蓄的反推。
设定理由: Sets reverse-thrust vibration with valid reverser and engine conditions. Zero removes the cue.
从慢车到全功率跟随转速的持续动力装置振动——前方有东西在烧油的永恒提醒。
调高: 杆里更多发动机。
调低: 更含蓄的发动机。
设定理由: Sets estimated engine vibration using configured telemetry and response, not measured cockpit vibration.
仅在模拟器报告襟翼舵面确实移动时的持续振动。它跟随真实作动器的运动和故障,而非估算的计时器。
调高: 襟翼移动中更多振动。
调低: 更含蓄的襟翼行程。
设定理由: Sets texture from observed flap movement; a command without movement does not establish the cue.
自动驾驶指令可以让杆实际移动多远。在MSFS中保持极小,因为移动的轴可能被读回为飞行员输入;零则完全禁用跟随。
调高: 自动驾驶让你的杆移动得明显更多。
调低: 几乎察觉不到的跟随。
设定理由: Sets admitted AP-follow gain, not a percentage of travel. Runtime ownership and input limits still apply.
Whether this feature is active in this profile.
设定理由: Applies the configured pitch and roll spring travel curves.
设定理由: Sets response at the second pitch-curve point; it is an endpoint only if its input position is full travel.
设定理由: Sets response at the second roll-curve point; its input position and other points determine the travel law.
Whether this feature is active in this profile.
设定理由: Retained for compatibility and group membership. Trim relief, rather than this flag, controls centre movement.
Whether this feature is active in this profile.
设定理由: Allows trim relief with supported control law and valid telemetry. Axis authorities set its amount.
Whether this feature is active in this profile.
设定理由: Enables local force trim, separate from aircraft-owned trim and add-on integration qualification.
Whether this feature is active in this profile.
设定理由: Allows load-factor changes to modify permitted spring laws. Passive fly-by-wire feel can suppress it.
Whether this feature is active in this profile.
设定理由: Enables rate damping with the configured coefficients and control law.
Whether this feature is active in this profile.
设定理由: Autopilot following is off; the configured spring and load retain the hardware feel. Separate neutral hold is on at strength 0.28, when a supported autopilot state admits it.
Whether this feature is active in this profile.
设定理由: Permits centering hold during a supported AP state, separate from following a moving target.
设定理由: Sets admitted AP neutral-hold strength; inactive while neutral hold is disabled.
Whether this feature is active in this profile.
设定理由: Enables aerodynamic cues; each still needs nonzero strength and its simulator conditions.
Where this effect reaches full strength (or has fully faded, for washouts).
调高: a more gradual build to a later peak.
调低: a quicker build.
设定理由: Sets the final flap index for detent normalization. UP plus three detents uses maximum index3.
Where this effect begins fading in.
调高: the effect begins later.
调低: it begins earlier.
设定理由: Sets the first flap detent that admits buffet; this is a handle index, not degrees.
Whether this feature is active in this profile.
设定理由: Permits shaker at supported warning conditions; the switch does not establish aircraft equipment.
Whether this feature is active in this profile.
设定理由: Enables ground effects; each still needs its own strength and contact or motion telemetry.
Whether this feature is active in this profile.
设定理由: Enables engine cues with nonzero settings and valid running-engine telemetry.
Whether this feature is active in this profile.
设定理由: Enables accessory cues with configured strengths and observed accessory movement.
The strength of this effect.
调高: a stronger effect.
调低: a weaker one.
设定理由: Sets texture from observed gear movement, separate from aerodynamic and touchdown effects.
| 参数 | 数值 | 控制作用及原因 |
|---|---|---|
| Spring strength | 0.55 | The fixed-centre choice represents an electronic-control inceptor. The baseline spring is 0.55. The electronic-control law keeps centering independent of airspeed. |
| Spring deadband | 0.01 | Sets travel around the centre before the baseline spring resists. Smaller values engage it sooner. |
| Forces · Center starting force | 0.03 | The centre preload is 0.03. It ramps outside the 0.01 deadband across 0.05 travel, shaping the passive centre independently of aircraft autotrim. |
| Forces · Center starting force transition | 0.05 | Sets the travel used to ramp in centre preload. Wider intervals make its onset more gradual. |
| Force gain | 0.04 | The stored 0.04 aerodynamic-load gain is inactive under the fixed-centre control law. |
| Master gain | 0.85 | Scales overall profile strength while preserving effect balance, subject to device and output limits. |
| Dynamic-pressure blend | False | Allows baseline spring strength to rise with indicated airspeed where the control law permits it. |
| Minimum spring factor | 0.5 | Sets low-speed spring strength as a fraction of baseline when blending is enabled. One keeps full strength. |
| Spring wake-up speed | 20 kt | Sets the IAS where the low-speed spring blend starts rising. This is a feel threshold, not a flight limit. |
| Spring full-strength speed | 90 kt | Sets the IAS where the low-speed blend reaches baseline strength; high-speed stiffening also uses it. |
| 力反馈调校速度 | 270.0 kt | Sets the IAS reference for aerodynamic loading. It is an estimate, not published cruise TAS or a flight limit. |
| Airspeed spring stiffening | 0 | Adds permitted spring resistance above the full-blend speed. Zero removes this high-speed increase. |
| Airspeed stiffening cap | 5 | Limits the squared airspeed ratio used for high-speed spring stiffening; it is not a device-force cap. |
| Aileron force scale | 1 | Roll and pitch aerodynamic scales are 1 and 1, respectively. These stored weights do not create directed aerodynamic loading while that term is inactive. The pitch spring-travel curve reaches output 1 at input 1. The roll spring-travel curve reaches output 0.3 at input 1. Spring-travel response contributes separately to axis balance. |
| Elevator force scale | 1 | Scales pitch aerodynamic loading; pitch spring travel and trim responses are separate settings. |
| Maximum output force | 0.55 | Caps directed-force output. Native spring effects and device limits remain separate. |
| SpringResponse · Travel enabled | True | Applies the configured pitch and roll spring travel curves. |
| SpringResponse · Output | 1 | Sets response at the second pitch-curve point; it is an endpoint only if its input position is full travel. |
| SpringResponse · Output | 0.3 | Sets response at the second roll-curve point; its input position and other points determine the travel law. |
| StickFeel · Trim feel enabled | False | Retained for compatibility and group membership. Trim relief, rather than this flag, controls centre movement. |
| StickFeel · Trim relief enabled | False | Allows trim relief with supported control law and valid telemetry. Axis authorities set its amount. |
| StickFeel · Elevator authority | 0 | Aircraft trim is separate from the configured hardware centre. Pitch relief is off, with stored authority 0; roll authority is 0. |
| StickFeel · Aileron authority | 0 | Scales supported roll-trim relief and permitted centre movement. Zero removes roll response. |
| StickFeel · Force trim enabled | False | Enables local force trim, separate from aircraft-owned trim and add-on integration qualification. |
| StickFeel · G load enabled | False | Allows load-factor changes to modify permitted spring laws. Passive fly-by-wire feel can suppress it. |
| StickFeel · Rate damping enabled | False | Enables rate damping with the configured coefficients and control law. |
| Autopilot · Follow enabled | False | Autopilot following is off; the configured spring and load retain the hardware feel. Separate neutral hold is on at strength 0.28, when a supported autopilot state admits it. |
| Autopilot · Follow authority | 0.05 | Sets admitted AP-follow gain, not a percentage of travel. Runtime ownership and input limits still apply. |
| Autopilot · Neutral hold enabled | True | Permits centering hold during a supported AP state, separate from following a moving target. |
| Autopilot · Neutral hold strength | 0.28 | Sets admitted AP neutral-hold strength; inactive while neutral hold is disabled. |
| Aero · Enabled | True | Enables aerodynamic cues; each still needs nonzero strength and its simulator conditions. |
| Aero · Gain | 0.06 | Sets stall-buffet strength. Zero removes the cue without changing simulator stalls or warnings. |
| Aero · Gain | 0.06 | Sets high-Mach buffet strength; onset and full-strength thresholds are separate. |
| Aero · Gain | 0 | Sets flap buffet at the configured position and speed gates. Flap movement texture is separate. |
| Aero · Max flap index | 3 | Sets the final flap index for detent normalization. UP plus three detents uses maximum index3. |
| Aero · Min flap index | 2 | Sets the first flap detent that admits buffet; this is a handle index, not degrees. |
| Aero · Gain | 0 | Sets gear aerodynamic buffet; movement and ground-contact cues are separate. |
| Aero · Shaker enabled | False | Permits shaker at supported warning conditions; the switch does not establish aircraft equipment. |
| Aero · Amplitude | 0.5 | Sets triggered shaker strength; inactive while the shaker feature is disabled. |
| Ground · Enabled | False | Enables ground effects; each still needs its own strength and contact or motion telemetry. |
| Ground · Gain | 0 | Sets rolling texture strength, modified by speed, surface and undercarriage configuration. |
| Ground · Gain | 0 | Sets gear-bump texture during ground motion, separate from touchdown impact. |
| Ground · Gain | 0 | Sets landing-impact strength; landing telemetry and response shape determine the pulse. |
| Ground · Gain | 0 | Sets reverse-thrust vibration with valid reverser and engine conditions. Zero removes the cue. |
| Engine · Enabled | False | Enables engine cues with nonzero settings and valid running-engine telemetry. |
| Engine · Gain | 0 | Sets estimated engine vibration using configured telemetry and response, not measured cockpit vibration. |
| Mechanical · Enabled | True | Enables accessory cues with configured strengths and observed accessory movement. |
| Mechanical · Gain | 0 | Sets texture from observed flap movement; a command without movement does not establish the cue. |
| Mechanical · Gain | 0 | Sets texture from observed gear movement, separate from aerodynamic and touchdown effects. |
如果你的真机经验表明本页有误,请在此指正。
本页基于引用资料构建,而真机经验胜过任何引用。 请引用有误的主张,并告诉我们真机的实际表现。纠错 将交由维护者审核,并纳入本研究的下一次修订。